[{"section":"Page","title":"About AANTC","url":"/","summary":"","meta":"","search_text":"about aantc centre center mission hkust","order":0,"static_url":"/"},{"section":"Page","title":"Research","url":"/research/all/","summary":"","meta":"","search_text":"research aerodynamics aeroacoustics low-altitude aircraft sports aerodynamics performance","order":1,"static_url":"/research/all/"},{"section":"Page","title":"Facilities & software","url":"/facility/all/","summary":"","meta":"","search_text":"facilities & software experimental facilities measurement platforms computational methods","order":2,"static_url":"/facility/all/"},{"section":"Page","title":"Team","url":"/team/","summary":"","meta":"","search_text":"team faculty research assistants fellows students alumni","order":3,"static_url":"/team/"},{"section":"Page","title":"Publications","url":"/publications/all/","summary":"","meta":"","search_text":"publications journal articles conference papers","order":4,"static_url":"/publications/all/"},{"section":"Page","title":"News","url":"/post/all/","summary":"","meta":"","search_text":"news research activity project visits collaborations","order":5,"static_url":"/post/all/"},{"section":"Page","title":"Opportunities","url":"/career/all/","summary":"","meta":"","search_text":"opportunities academic research professional vacancies careers","order":6,"static_url":"/career/all/"},{"section":"Page","title":"Contact AANTC","url":"/contact/","summary":"","meta":"","search_text":"contact aantc address visit hkust map","order":7,"static_url":"/contact/"},{"section":"Page","title":"Privacy","url":"/privacy/","summary":"","meta":"","search_text":"privacy privacy cookies local storage analytics personal data","order":8,"static_url":"/privacy/"},{"section":"Page","title":"Accessibility","url":"/accessibility/","summary":"","meta":"","search_text":"accessibility accessibility keyboard screen reader zoom reduced motion","order":9,"static_url":"/accessibility/"},{"section":"Research","title":"Contra-rotating rotor PIV measurements","url":"/research/62/","summary":"Contra-rotating rotors in advanced unmanned aerial vehicles (UAVs) can offer enhanced aerodynamic performance and pose significant aeroacoustics challenges. This study experimentally investigates the far-field noise characteristics and flow-field of a 21.8 cm diameter contra-rot…","meta":"Aeroacoustics","search_text":"contra-rotating rotor piv measurements contra-rotating rotors in advanced unmanned aerial vehicles (uavs) can offer enhanced aerodynamic performance and pose significant aeroacoustics challenges. this study experimentally investigates the far-field noise characteristics and flow-field of a 21.8 cm diameter contra-rotating rotors system during axial descent with the effects of varying rotational speeds (60–100 rps) and descent rates (vd from 0 m/s to 12 m/s). experimental results show that the contra-rotating rotor noise increase slightly at low descent rates, decrease sharply at descent ratio vd/vh around 1.8 (vd/vh is defined as descent speed divided by induced speed while hovering), and rise again when vd/vh>2. directivity results exhibit a dipole characteristic. tonal noise i aeroacoustics contra-rotating rotors in advanced unmanned aerial vehicles (uavs) can offer enhanced aerodynamic performance and pose significant aeroacoustics challenges. this study experimentally investigates the far-field noise characteristics and flow-field of a 21.8 cm diameter contra-rotating rotors system during axial descent with the effects of varying rotational speeds (60–100 rps) and descent rates (vd from 0 m/s to 12 m/s). experimental results show that the contra-rotating rotor noise increase slightly at low descent rates, decrease sharply at descent ratio vd/vh around 1.8 (vd/vh is defined as descent speed divided by induced speed while hovering), and rise again when vd/vh>2. directivity results exhibit a dipole characteristic. tonal noise i cheng cao, zhida ma, xiangtian li, wangqiao chen, peng zhou and xin zhang","order":10,"static_url":"/research/62/"},{"section":"Research","title":"An experimental study of rotor aeroacoustics with aeroelastic effects under edgewise flight conditions","url":"/research/61/","summary":"Rotor blades in eVTOL aircraft are often assumed rigid in noise studies, but their thin, slender design makes them prone to large aeroelastic deformations during edgewise forward flight. Measurements in an anechoic wind tunnel showed that a thin-root variant (lower flapwise stif…","meta":"Aeroacoustics","search_text":"an experimental study of rotor aeroacoustics with aeroelastic effects under edgewise flight conditions rotor blades in evtol aircraft are often assumed rigid in noise studies, but their thin, slender design makes them prone to large aeroelastic deformations during edgewise forward flight. measurements in an anechoic wind tunnel showed that a thin-root variant (lower flapwise stiffness) of a 229 mm baseline rotor experiences significantly greater time-varying deformations, resulting in a reduced broadband noise compared to the baseline. wavelet-based beamforming confirmed the advancing blade as the dominant noise source, with the broadband reduction linked to weakened blade-vortex interactions, improving understanding of how blade flexibility affects evtol rotor acoustics. aeroacoustics rotors are the primary noise contributors in evtol aircraft. investigations into rotor noise problems often assume that rotor blades are rigid, neglecting their aeroelastic effects. however, rotor blades are typically designed to be thin and slender for improved aerodynamic efficiency. this makes them highly susceptible to aeroelastic deformations, especially during edgewise forward flight. in this work, we investigate the aerodynamic and aeroacoustic performance of a baseline rotor with a diameter of 229 mm and its thin-root variant, which has significantly lower flapwise stiffness. the measurements were conducted in an anechoic wind tunnel under edgewise forward flight conditions. first, deformation measurements reveal that the thin-root rotor experiences significantly larger time varying deformations. then, acoustic measurements indicate that the thin-root rotor produces a higher blade-passing frequency (bpf) tone and a lower broadband noise level compared with the baseline. next, results from a wavelet-based beamforming method show that the advancing blade is the primary noise source, with the reduction in broadband noise attributed to weakened blade-vortex interaction (bvi). these findings enhance our understanding of the impact of rotor blade deformation on evtol rotor acoustics. zhenjun peng, wangqiao chen, bao chen, puyuan wang, peng zhou, xin zhang contours of axial deflection for the thin-root rotor and the baseline rotor at tilt angles phase-averaged acoustic imaging results from t = 0.2t to t = 0.3t. phase-averaged acoustic imaging results from t = 0.2t to t = 0.4t.","order":11,"static_url":"/research/61/"},{"section":"Research","title":"Windsurfing CFD","url":"/research/54/","summary":"AANTC has developed an efficient computational fluid dynamics (CFD) platform for sports aerodynamics research, including windsurfing. The windsurfing project focuses on the equipment that will be used for the 2024 Olympics. The specificity of this new windsurfing equipment is th…","meta":"Sports Aerodynamics","search_text":"windsurfing cfd aantc has developed an efficient computational fluid dynamics (cfd) platform for sports aerodynamics research, including windsurfing. the windsurfing project focuses on the equipment that will be used for the 2024 olympics. the specificity of this new windsurfing equipment is that the submerged hydrofoil provides vertical lift and allows the windsurfer and the board to lift above the water surface and hence attain faster speeds. the robust large-scale simulations evaluate both the aerodynamic and hydrodynamic performances of the sail, athlete, and hydrofoil. sports aerodynamics aantc has developed an efficient computational fluid dynamics (cfd) platform for sports aerodynamics research, including windsurfing. the windsurfing project focuses on the equipment that will be used for the 2024 olympics. the specificity of this new windsurfing equipment is that the submerged hydrofoil provides vertical lift and allows the windsurfer and the board to lift above the water surface and hence attain faster speeds. the robust large-scale simulations evaluate both the aerodynamic and hydrodynamic performances of the sail, athlete, and hydrofoil. the simulations have the capabilities and specifications of: ─ simulation of sail motion; ─ high-quality dynamically deforming mesh; ─ two-phase flow simulation for the sail and the hydrofoil; ─ advanced simulation and post-processing schemes;","order":12,"static_url":"/research/54/"},{"section":"Research","title":"Low-noise UAM planning in the community","url":"/research/59/","summary":"Drones are promising transport means for the last-mile deliveries in urban communities. However, low-altitude aviation can cause severe noise pollution, leading to the requirement of rational operational strategies to minimize noise emissions. In this work, the noise impact on a…","meta":"Aeroacoustics","search_text":"low-noise uam planning in the community drones are promising transport means for the last-mile deliveries in urban communities. however, low-altitude aviation can cause severe noise pollution, leading to the requirement of rational operational strategies to minimize noise emissions. in this work, the noise impact on an urban community of delivery drones is assessed using a virtual flight platform that contains noise generation and projection modules. both the tonal and broadband noise components are taken into account via analytical and semi-empirical prediction methods, and the noise propagation in the urban environment is computed by an efficient gaussian beam tracing method. aeroacoustics drones are promising transport means for the last-mile deliveries in urban communities. however, low-altitude aviation can cause severe noise pollution, leading to the requirement of rational operational strategies to minimize noise emissions. in this work, the noise impact on an urban community of delivery drones is assessed using a virtual flight platform that contains noise generation and projection modules. both the tonal and broadband noise components are taken into account via analytical and semi-empirical prediction methods, and the noise propagation in the urban environment is computed by an efficient gaussian beam tracing method.","order":13,"static_url":"/research/59/"},{"section":"Research","title":"Acoustic liners for modern aero-engine noise reduction","url":"/research/58/","summary":"Attenuating the low-frequency component of aero-engine noise is challenging due to the mass and volume constraints when applying conventional noise mitigation techniques using liners and foams. To address it, acoustic liners constructed by Helmholtz resonators with extended neck…","meta":"Acoustic materials","search_text":"acoustic liners for modern aero-engine noise reduction attenuating the low-frequency component of aero-engine noise is challenging due to the mass and volume constraints when applying conventional noise mitigation techniques using liners and foams. to address it, acoustic liners constructed by helmholtz resonators with extended necks (hrens) are developed. an analytical noise reduction model of this kind of liners are established through combining the equivalent medium model and the transfer matrix method, based on which inhomogeneous liners design methodology for maximizing the attenuation capability was developed. to investigate the aerodynamic and aeroacoustic performance of the liners subjected to high-intensity incidence, an advanced grazing flow tube was built up with the incident spl acoustic materials attenuating the low-frequency component of aero-engine noise is challenging due to the mass and volume constraints when applying conventional noise mitigation techniques using liners and foams. to address it, acoustic liners constructed by helmholtz resonators with extended necks (hrens) are developed. an analytical noise reduction model of this kind of liners are established through combining the equivalent medium model and the transfer matrix method, based on which inhomogeneous liners design methodology for maximizing the attenuation capability was developed. to investigate the aerodynamic and aeroacoustic performance of the liners subjected to high-intensity incidence, an advanced grazing flow tube was built up with the incident spl","order":14,"static_url":"/research/58/"},{"section":"Research","title":"Acoustic meta-surface development","url":"/research/57/","summary":"A series of acoustic metasurfaces with periodic structures are proposed using porous materials including meta-based fibrous materials and polymer foam to refract an incidence wave in an anomalous yet controllable way.","meta":"Acoustic materials","search_text":"acoustic meta-surface development a series of acoustic metasurfaces with periodic structures are proposed using porous materials including meta-based fibrous materials and polymer foam to refract an incidence wave in an anomalous yet controllable way. acoustic materials a series of acoustic metasurfaces with periodic structures are proposed using porous materials including meta-based fibrous materials and polymer foam to refract an incidence wave in an anomalous yet controllable way. in one period, there are several elements responding to incident wave differently. through carefully designing the individual elements, the reflected or refracted waves can be manipulated. the anomalous behaviours are predicted theoretically and validated by numerical simulations and laboratory tests. based on the capability of wave manipulation, the acoustic energy can be prevented from radiating into the far field, resulting in effective noise control. considering aeroacoustic applications, e.g. acoustic liners in engines, the studies on the effects of grazing-incidence acoustic waves and flow on the metasurfaces are being implemented.","order":15,"static_url":"/research/57/"},{"section":"Research","title":"Computational Aerodynamics of Cyclists","url":"/research/56/","summary":"This research combines numerical simulation with controlled wind-tunnel measurements to investigate cycling aerodynamics. The computational work resolves flow structures around cyclist-bicycle configurations and examines how posture, crosswinds, wheel design and cyclist spacing …","meta":"Sports Aerodynamics","search_text":"computational aerodynamics of cyclists this research combines numerical simulation with controlled wind-tunnel measurements to investigate cycling aerodynamics. the computational work resolves flow structures around cyclist-bicycle configurations and examines how posture, crosswinds, wheel design and cyclist spacing affect aerodynamic forces and wake behaviour. the results support the interpretation of experiments and the aerodynamic assessment of cycling equipment and race configurations. sports aerodynamics aantc uses computational fluid dynamics to study airflow around cyclists, bicycles and cycling equipment. numerical flow fields reveal wake development and aerodynamic interactions associated with riding posture, leg position, wheel configuration and the relative position of cyclists. computational models provide three-dimensional descriptions of the flow around cyclist-bicycle systems. the simulations identify flow separation, vortical structures and wake development around the rider and bicycle, giving physical context to measured forces. related studies address complete cyclist geometries, individual wheel configurations and aerodynamic interactions between cyclists. wind-tunnel measurements provide an experimental reference for selected numerical studies. published work compares computed and measured aerodynamic forces, and uses wake measurements to examine the corresponding flow structures. particle image velocimetry provides an additional comparison for studies of cycling-wheel wakes. together, these methods connect computed flow fields with measurable aerodynamic behaviour and support the careful assessment of posture, equipment and race configurations.","order":16,"static_url":"/research/56/"},{"section":"Research","title":"High-accuracy wind tunnel test","url":"/research/55/","summary":"The cycling aerodynamic test rig was designed and built in 2018. It incorporates the knowledge and experience of more than twenty years’ R&D effort in aerospace engineering and racing car engineering, led by Prof. Xin Zhang. The test rig is used to measure the aerodynamic forces…","meta":"Sports Aerodynamics","search_text":"high-accuracy wind tunnel test the cycling aerodynamic test rig was designed and built in 2018. it incorporates the knowledge and experience of more than twenty years’ r&d effort in aerospace engineering and racing car engineering, led by prof. xin zhang. the test rig is used to measure the aerodynamic forces acting on a cyclist in the wind. a custom-built, high-accuracy balance is used to withstand the large unsteady pedalling force exerted by the athlete and resolve small changes in aerodynamic forces. the test rig has been used to evaluate cycling equipment and athlete performance. in addition, by combining with the cycling mannequin developed by the team in 2019, new cycling skinsuits and equipment were evaluated using the test rig. sports aerodynamics the cycling aerodynamic test rig was designed and built in 2018. it incorporates the knowledge and experience of more than twenty years’ r&d effort in aerospace engineering and racing car engineering, led by prof. xin zhang. the test rig is used to measure the aerodynamic forces acting on a cyclist in the wind. a custom-built, high-accuracy balance is used to withstand the large unsteady pedalling force exerted by the athlete and resolve small changes in aerodynamic forces. the test rig has been used to evaluate cycling equipment and athlete performance. in addition, by combining with the cycling mannequin developed by the team in 2019, new cycling skinsuits and equipment were evaluated using the test rig. the rig has the following capability: ─ six-component high-accuracy balance; ─ instrumentation for rotational torque measurement; ─ low-interference aero bike supporting struts; ─ suitable for both athlete and cycling equipment tests; ─ embedded turbo trainer for realistic test condition.","order":17,"static_url":"/research/55/"},{"section":"Research","title":"Aerodynamic design of sports equipment","url":"/research/53/","summary":"The CFD simulation platform and the wind tunnel test rig are seamlessly integrated for equipment development, following established procedures in aerospace engineering and racing car engineering. The automated CFD platform is used to run a multitude of simulations, between which…","meta":"Sports Aerodynamics","search_text":"aerodynamic design of sports equipment the cfd simulation platform and the wind tunnel test rig are seamlessly integrated for equipment development, following established procedures in aerospace engineering and racing car engineering. the automated cfd platform is used to run a multitude of simulations, between which the geometry of the cycling is modified for aerodynamic improvement. prototypes are then fabricated and tested in the wind tunnel. design iterations are conducted to provide incremental gains of the aerodynamic performance while satisfying structural requirements. sports aerodynamics the cfd simulation platform and the wind tunnel test rig are seamlessly integrated for equipment development, following established procedures in aerospace engineering and racing car engineering. the automated cfd platform is used to run a multitude of simulations, between which the geometry of the cycling is modified for aerodynamic improvement. prototypes are then fabricated and tested in the wind tunnel. design iterations are conducted to provide incremental gains of the aerodynamic performance while satisfying structural requirements.","order":18,"static_url":"/research/53/"},{"section":"Research","title":"Owl inspired material for trailing edge noise control","url":"/research/25/","summary":"Owls are known as silent predators of the night. Compared to other famous raptors such as falcons and kestrels, owls are not fast at all. Instead, after millions of evolution, owls have special adaptations which enable them to approach to their prey with little noise. In particu…","meta":"Aeroacoustics","search_text":"owl inspired material for trailing edge noise control owls are known as silent predators of the night. compared to other famous raptors such as falcons and kestrels, owls are not fast at all. instead, after millions of evolution, owls have special adaptations which enable them to approach to their prey with little noise. in particular, owls’ feathers have three unique features: leading edge serrations, trailing edge fringes, as well as the hairy dorsal surface. the function of the last feature is not well understood, and no related application is known. aeroacoustics the evolution in the past millions of years enables owls to reduce their flight noise efficiently, especially in the high-frequency range, where their preys are most sensitive. owls’ feathers have three unique features: leading edge serrations, trailing edge fringes, as well as the hairy dorsal surface. in this research, artificial hairy structures are fabricated to resemble owls' downy feather. these structures are attached to a flat plate test model to study there effect on trailing edge noise. the hairy coating can significantly reduce the high-frequency noise generated at the trailing edge. a theoretical model was developed to predict the noise radiation with the turbulence information obtained by the wake measurement using the hot-wire. peng zhou and gonam lui the microstructure of the velvet structure on an eagle owl's primary feather. setup of the acoustic measurement in the anechoic wind tunnel. comparison of the third-octave acoustic images of the clean and hairy flat plate models.","order":19,"static_url":"/research/25/"},{"section":"Research","title":"Sliding grid simulation of cascade noise","url":"/research/30/","summary":"Turbofan engines are commonly used on modern commercial aircrafts and have become a significant source of noise pollution. The tonal noise generated by turbofan engines has been extensively studied, and noise reduction approaches such as acoustic liners have been developed. The …","meta":"Aeroacoustics","search_text":"sliding grid simulation of cascade noise turbofan engines are commonly used on modern commercial aircrafts and have become a significant source of noise pollution. the tonal noise generated by turbofan engines has been extensively studied, and noise reduction approaches such as acoustic liners have been developed. the dominant source of broadband noise is due to the turbulent fan-wake interacting with the leading edges of the outlet guide vanes (ogv) aeroacoustics the rotational motion of the fan blades was considered, by applying a high-order hybrid sliding interface between the turbulence injection region and the ogvs. the effect of the advance ratio and turbulence properties of the fanwakes, such as the wake width and turbulent integral length scale, on the sound power level, were investigated. the sound power level obtained are compared to analytical predictions. the wake rotation speed has no significant effect on the noise generated by the cascade, due to the similar levels of averaged turbulence intensity across each case. this will remain true, as long as the separation between adjacent wakes is a constant. the changes in the wake width have a significant influence on the upstream and downstream sound power levels. wider wakes tend to increase the pwl at low frequencies and decrease the levels at high frequencies. similar effects were observed for the downstream pwl spectra. wei ying, ryu fattah","order":20,"static_url":"/research/30/"},{"section":"Research","title":"Rotor aeroacoustics","url":"/research/49/","summary":"Systematic rotor noise study is conducted in AANTC including analytical measurement, numerical simulation and experimental measurements. Theoretical noise prediction models are developed to compute the noise radiation from propellers at different working conditions. Recently, th…","meta":"Aeroacoustics","search_text":"rotor aeroacoustics systematic rotor noise study is conducted in aantc including analytical measurement, numerical simulation and experimental measurements. theoretical noise prediction models are developed to compute the noise radiation from propellers at different working conditions. recently, the effects of unsteady motions and uncertainty factors are considered in the theoretical model. aeroacoustics systematic rotor noise study is conducted in aantc including analytical measurement, numerical simulation and experimental measurements. theoretical noise prediction models are developed to compute the noise radiation from propellers at different working conditions. recently, the effects of unsteady motions and uncertainty factors are considered in the theoretical model. the numerical simulation is mainly based on the acoustic-wave preserved artificial compressibility method to compute the sound generation in different working conditions. the study leads to low-noise blade designs. the experimental study is based on the anechoic facilities in the group. the effects of blade geometry, low-noise treatment and wind conditions are systematic different rotors are designed in aantc, and the aerodynamic and aeroacoustic performances are measured. some data study are available for academic purposes upon reasonable request.","order":21,"static_url":"/research/49/"},{"section":"Research","title":"Drone noise measurements","url":"/research/50/","summary":"The noise radiation from unmanned aerial vehicles is measured in both anechoic chamber and outdoor environments. The effects of microphone arrangement, data processing method, requirements on whether condition, flight accuracy are studied. The effect of the working different wor…","meta":"Aeroacoustics","search_text":"drone noise measurements the noise radiation from unmanned aerial vehicles is measured in both anechoic chamber and outdoor environments. the effects of microphone arrangement, data processing method, requirements on whether condition, flight accuracy are studied. the effect of the working different working conditions, and weight and the imbalance are measured. the noise sources and the directivity patterns are measured. the outcome of the measurement partly supports the development of iso standard on noise assessment led by the research group. aeroacoustics the noise radiation from unmanned aerial vehicles is measured in both anechoic chamber and outdoor environments. the effects of microphone arrangement, data processing method, requirements on whether condition, flight accuracy are studied. the effect of the working different working conditions, and weight and the imbalance are measured. the noise sources and the directivity patterns are measured. the outcome of the measurement partly supports the development of iso standard on noise assessment led by the research group. the outcome of the measurement partly supports the development of iso standard on noise assessment led by the research group.","order":22,"static_url":"/research/50/"},{"section":"Research","title":"Bluff-body aerodynamic drag and noise reduction","url":"/research/51/","summary":"Aerodynamic and aeroacoustic characteristics of a cylinder with longitudinal grooves were studied in an anechoic wind tunnel, emphasizing on drag and noise attenuation. The parallel mounted load cells and a single microphone measured the aerodynamic resistance and noise of a cir…","meta":"Sports Aerodynamics","search_text":"bluff-body aerodynamic drag and noise reduction aerodynamic and aeroacoustic characteristics of a cylinder with longitudinal grooves were studied in an anechoic wind tunnel, emphasizing on drag and noise attenuation. the parallel mounted load cells and a single microphone measured the aerodynamic resistance and noise of a circular cylinder with longitudinal grooves at reynolds number ranging from 5.84 × 10^4 to 8.48 × 10^4, covering the flow regimes from the sub-critical to the post-critical states. the results show that longitudinal grooves can effectively trigger the boundary-layer transition started at a reynolds number around 5.84 × 10^4, causing the so-called drag crisis. during the transition process, a drag reduction over 50% and a maximum noise attenuation over 15 db can be achieved sports aerodynamics aerodynamic and aeroacoustic characteristics of a cylinder with longitudinal grooves were studied in an anechoic wind tunnel, emphasizing on drag and noise attenuation. the parallel mounted load cells and a single microphone measured the aerodynamic resistance and noise of a circular cylinder with longitudinal grooves at reynolds number ranging from 5.84 × 10^4 to 8.48 × 10^4, covering the flow regimes from the sub-critical to the post-critical states. the results show that longitudinal grooves can effectively trigger the boundary-layer transition started at a reynolds number around 5.84 × 10^4, causing the so-called drag crisis. during the transition process, a drag reduction over 50% and a maximum noise attenuation over 15 db can be achieved","order":23,"static_url":"/research/51/"},{"section":"Research","title":"Aeroacoustics of obstructions in turbulent boundary layers","url":"/research/52/","summary":"The aerodynamic noise generated by a two-dimensional large obstacle in a turbulent boundary layer. The obstacles have different shape and height emerged in the turbulent boundary layer of the flat plate. The spectra of turbulence and sound in a wide velocity range of 20-50m/s wa…","meta":"Aeroacoustics","search_text":"aeroacoustics of obstructions in turbulent boundary layers the aerodynamic noise generated by a two-dimensional large obstacle in a turbulent boundary layer. the obstacles have different shape and height emerged in the turbulent boundary layer of the flat plate. the spectra of turbulence and sound in a wide velocity range of 20-50m/s was tested. scaling laws of the turbulence and acoustic results are conducted, and the noise generation mechanisms are analysed. aeroacoustics the aerodynamic noise generated by a two-dimensional large obstacle in a turbulent boundary layer. the obstacles have different shape and height emerged in the turbulent boundary layer of the flat plate. the spectra of turbulence and sound in a wide velocity range of 20-50m/s was tested. scaling laws of the turbulence and acoustic results are conducted, and the noise generation mechanisms are analysed.","order":24,"static_url":"/research/52/"},{"section":"Research","title":"Sound Extrapolation Method for Turbulent Flows","url":"/research/26/","summary":"In aeroacoustics, the far-field directivity is often computed using the integral solution of the acoustic analogy equations. The sound prediction can be rendered when the turbulent eddies move across the integration surface, and the expensive volume integral terms are neglected.","meta":"Aeroacoustics","search_text":"sound extrapolation method for turbulent flows in aeroacoustics, the far-field directivity is often computed using the integral solution of the acoustic analogy equations. the sound prediction can be rendered when the turbulent eddies move across the integration surface, and the expensive volume integral terms are neglected. aeroacoustics in computational aeroacoustics (caa), the acoustic directivity patterns using the so-called hybrid methods. the near-field fluid/acoustic field is resolved using the high-accuracy numerical simulations while the sound extrapolation methods (or sometimes it is called sound projection methods) to account for the sound radiation processes. usually, the integral solution of the well-known ffowcs-williams and hawkings (fw-h) equation (proc. r. soc. a., vol. 264, no. 1151, p. 321-342, 1969), which is one of the most important equations in the subject of aeroacoustics, is often employed for the hybrid computation. it is an exact rearrangement of the fluid governing equations, and it could provide the exact acoustic solution in case that the equation is exactly solved. however, in practical applications, the volume integral term is often omitted to save the computational expense and to avoid the difficulty of “cause-and-effect” issue (that unknowns appear in the source terms). one consequence of neglecting the volume terms is that the predicted sound field can be contaminated when the permeable integration surface is located in the turbulent flows. there were fw-h equation-based methods such as using on-body or open integration surfaces, which, however, have limitations in certain circumstances. at aantc, a series of studies were conducted to propose new sound projection methods that are suitable for turbulent flow applications. the key idea of the trend of studies is to filter out the non-acoustic (or acoustically inefficient) components in the turbulent flows before the various are employed for acoustic far-field computation. the idea is based on our understanding of that the turbulent flow fluctuations can be decomposed into the acoustical, vortical and entropy components (kovasznay, j. aero. sci., vol. 20, no. 1 the initial study focused on filtering out the vortical components by developing a variant of the lighthill’s acoustic analogy (proc. r. soc. a., vol. 211, p. 546-578, 1952), in which the mean flow is considered, and the fluctuations are defined based on the local mean flow components. in the source term, divergence and convection operators are acting on the velocity components such that the vortical velocities are filtered out. the method is suitable for the turbulent flow dominated by the vortical components, and it was applied to the airfoil-gust interaction problems, in both subsonic and transonic flows [1]. siyang zhong","order":25,"static_url":"/research/26/"},{"section":"Research","title":"Aircraft airframe noise: Aerodynamics and aeroacoustics of a flap side-edge","url":"/research/44/","summary":"An experimental and computational investigation was carried out to determine the aerodynamics and aeroacoustics of a flap side-edge.","meta":"Aeroacoustics","search_text":"aircraft airframe noise: aerodynamics and aeroacoustics of a flap side-edge an experimental and computational investigation was carried out to determine the aerodynamics and aeroacoustics of a flap side-edge. aeroacoustics an experimental and computational investigation was carried out to determine the aerodynamics and aeroacoustics of a flap side-edge. a porous side-edge treatment was applied to the flap side-edge in an attempt to reduce airframe noise. the application of a porous flap side-edge had two favourable effects. firstly, it reduced the magnitude of vorticity in the turbulent shear layer and the vortex. this reduced the magnitude of the hydrodynamic instabilities induced by the flap side-edge vortex. secondly, it displaced the vortex further away from the flap surface due to the finite mass flux allowed through the porous material. this reduced the magnitude of the disturbances that interacted with the solid flap surface by moving them further away. this research was focused on understanding noise generation mechanisms associated with the flowfield around a flap-side edge and their reduction. previous investigations identified a noise reduction of up to 4 db in the far-field, within a limited band of frequencies, by replacing part of a flap side-edge with an open cell porous material. the physics responsible for this were not discussed. this work employed a variety of experimental and numerical techniques to understand the physics responsible for noise production at the flap side-edge and the mechanism by which a porous material applied to the flap side-edge reduced the noise.","order":26,"static_url":"/research/44/"},{"section":"Research","title":"Variable impedance liners for aero-engines","url":"/research/29/","summary":"Acoustic liners application within the nacelle walls is a well established passive noise damping technique in modern turbofan engine. Improved acoustic liners should be developed to improve the maximum noise attenuation induced by acoustic liners and broaden the attenuation freq…","meta":"Aeroacoustics","search_text":"variable impedance liners for aero-engines acoustic liners application within the nacelle walls is a well established passive noise damping technique in modern turbofan engine. improved acoustic liners should be developed to improve the maximum noise attenuation induced by acoustic liners and broaden the attenuation frequency range by using non-uniform acoustic liners. aeroacoustics the high bypass ratio of modern turbofan engine results in that the tonal noise decrease while the broadband noise is becoming a more and more important contributor in engine noise. thus improved acoustic liners should be develop to: 1. improve the maximum noise attenuation induced by acoustic liners. 2. broaden the attenuation frequency range by using non-uniform acoustic liners. engine intake noise radiation: in the m24n1 case study with no acoustic liner treatment, the bulk of the acoustic energy is concentrated towards the upper wall. as the wave propagates across the inlet there is no change in the acoustic wavelength. however, the wave is diffracted by duct lip. non-uniform liner distribution: the possibility of reducing radiated noise by varying the liner properties along the duct in both axial and circumferential directions was investigated. a serrated joint liner distribution was proposed jingwen guo and ryu fattah pressure contour of a lined intake duct for m24n1 directivity comparison of rigid wall and","order":27,"static_url":"/research/29/"},{"section":"Research","title":"Racing car aerodynamics: Aerodynamics of oscillating wings","url":"/research/33/","summary":"Wings in pitching motion can reach very large incidences, often overshooting the static stall angle. In those cases, the unsteady motion can be beneficial to the aerodynamic performance of the wing.","meta":"Sports Aerodynamics","search_text":"racing car aerodynamics: aerodynamics of oscillating wings wings in pitching motion can reach very large incidences, often overshooting the static stall angle. in those cases, the unsteady motion can be beneficial to the aerodynamic performance of the wing. sports aerodynamics wings in pitching motion can reach very large incidences, often overshooting the static stall angle. in those cases, the unsteady motion can be beneficial to the aerodynamic performance of the wing. lift can be enhanced and stall can be delayed to higher angles of attack. that process is known as dynamic stall. the dynamic stall process is not limited to an overshoot of lift at incidences above the static stall angle. exceeding that angle results in a leading edge vortex being formed (dynamic stall vortex) and convected downstream. the vortex induces an even lower pressure region on the suction surface, further increasing the lift but also creating a large pitching-down moment and increased drag. once the dynamic stall vortex is shed into t","order":28,"static_url":"/research/33/"},{"section":"Research","title":"Racing car aerodynamics: Aerodynamic interaction between a wing and wheels","url":"/research/34/","summary":"What is the influence of an upstream-mounted wing on the aerodynamic characteristics of a wheel and vice versa? How does the aerodynamic interaction between these components of the configuration depend on vertical, streamwise and spanwise position variations of the wing relative…","meta":"Sports Aerodynamics","search_text":"racing car aerodynamics: aerodynamic interaction between a wing and wheels what is the influence of an upstream-mounted wing on the aerodynamic characteristics of a wheel and vice versa? how does the aerodynamic interaction between these components of the configuration depend on vertical, streamwise and spanwise position variations of the wing relative to the wheel? which flow mechanisms and phenomena cause the observed behaviour and what would be the main factors of influence for these physics? would it be possible to reproduce the qualitative (flow features and phenomena) and quantitative (correlation with experimental results) aspects of wing-wheel interaction with the use of current, 'state-of-the-art' cfd simulations? sports aerodynamics what is the influence of an upstream-mounted wing on the aerodynamic characteristics of a wheel and vice versa? how does the aerodynamic interaction between these components of the configuration depend on vertical, streamwise and spanwise position variations of the wing relative to the wheel? which flow mechanisms and phenomena cause the observed behaviour and what would be the main factors of influence for these physics? would it be possible to reproduce the qualitative (flow features and phenomena) and quantitative (correlation with experimental results) aspects of wing-wheel interaction with the use of current, 'state-of-the-art' cfd simulations?","order":29,"static_url":"/research/34/"},{"section":"Research","title":"Racing car aerodynamics: Wheel aerodynamics","url":"/research/35/","summary":"Forty percent of the total drag on a Formula 1 car comes from the wheels. Wheels have an influence on the aerodynamics of the car as a whole, the front and rear wings, the under-body and the diffuser. The wheels are a source of noise above 40 miles per hour and they are the domi…","meta":"Sports Aerodynamics","search_text":"racing car aerodynamics: wheel aerodynamics forty percent of the total drag on a formula 1 car comes from the wheels. wheels have an influence on the aerodynamics of the car as a whole, the front and rear wings, the under-body and the diffuser. the wheels are a source of noise above 40 miles per hour and they are the dominant source of road vehicles. sports aerodynamics forty percent of the total drag on a formula 1 car comes from the wheels. wheels have an influence on the aerodynamics of the car as a whole, the front and rear wings, the under-body and the diffuser. the wheels are a source of noise above 40 miles per hour and they are the dominant source of road vehicles.","order":30,"static_url":"/research/35/"},{"section":"Research","title":"Racing car aerodynamics: Large-scale source term modelling of vortex generation","url":"/research/36/","summary":"For efficiency/affordability, the wind tunnel testing is expensive and comprehensive testing is impractical. Computational fluid dynamics (CFD) is useful while adapting grids are difficult and time consuming. In this case we do not mesh the vortex generating device but model its…","meta":"Sports Aerodynamics","search_text":"racing car aerodynamics: large-scale source term modelling of vortex generation for efficiency/affordability, the wind tunnel testing is expensive and comprehensive testing is impractical. computational fluid dynamics (cfd) is useful while adapting grids are difficult and time consuming. in this case we do not mesh the vortex generating device but model its effects via source terms (body forces) as an easy optimisation. sports aerodynamics for efficiency/affordability, the wind tunnel testing is expensive and comprehensive testing is impractical. computational fluid dynamics (cfd) is useful while adapting grids are difficult and time consuming. in this case we do not mesh the vortex generating device but model its effects via source terms (body forces) as an easy optimisation.","order":31,"static_url":"/research/36/"},{"section":"Research","title":"Aircraft airframe noise: Computational aeroaoustics of bogie noise","url":"/research/37/","summary":"Airframe noise is one of the main noise sources during the approach phase. Flight tests have shown that for large aircraft the main landing gear (MLG) is a dominant airframe noise source . The design of landing gear is primarily focussed on its mechanical function, which results…","meta":"Aeroacoustics","search_text":"aircraft airframe noise: computational aeroaoustics of bogie noise airframe noise is one of the main noise sources during the approach phase. flight tests have shown that for large aircraft the main landing gear (mlg) is a dominant airframe noise source . the design of landing gear is primarily focussed on its mechanical function, which results in a shape that is not very aerodynamic. this creates a lot of separated and turbulent flow and thus a lot of aeroacoustic noise. wind tunnel tests have revealed that the bogie beam as one of the most important noise sources of the main landing gear. the main objective of the project is to investigate the influence of bogie beam inclination angle on the flow field around the main landing gear and the noise generated by this flow. aeroacoustics airframe noise is one of the main noise sources during the approach phase. flight tests have shown that for large aircraft the main landing gear (mlg) is a dominant airframe noise source . the design of landing gear is primarily focussed on its mechanical function, which results in a shape that is not very aerodynamic. this creates a lot of separated and turbulent flow and thus a lot of aeroacoustic noise. wind tunnel tests have revealed that the bogie beam as one of the most important noise sources of the main landing gear. the main objective of the project is to investigate the influence of bogie beam inclination angle on the flow field around the main landing gear and the noise generated by this flow.","order":32,"static_url":"/research/37/"},{"section":"Research","title":"Aircraft airframe noise: Effect of bogie inclination on the unsteady flow field and noise production","url":"/research/38/","summary":"Computational methods are used to determine the flow field around a simplified landing gear geometry and the far field noise levels generated by this flow. The focus of this research is on the influence of bogie inclination angle on the flow features and the far field noise leve…","meta":"Aeroacoustics","search_text":"aircraft airframe noise: effect of bogie inclination on the unsteady flow field and noise production computational methods are used to determine the flow field around a simplified landing gear geometry and the far field noise levels generated by this flow. the focus of this research is on the influence of bogie inclination angle on the flow features and the far field noise levels. a high quality hybrid grid of eight million cells was generated around a simplified main landing gear geometry. a structured grid consisting of 5.5 million cells are applied to regions near the geometry where complex flow features are expected. aeroacoustics computational methods are used to determine the flow field around a simplified landing gear geometry and the far field noise levels generated by this flow. the focus of this research is on the influence of bogie inclination angle on the flow features and the far field noise levels. a high quality hybrid grid of eight million cells was generated around a simplified main landing gear geometry. a structured grid consisting of 5.5 million cells are applied to regions near the geometry where complex flow features are expected. the unstructured grid of 2.5 million cells are applied to extend the domain so that appropriate boundary conditions to be applied. a hybrid grid provides a high resolution of the flow features near the bluff body geometry, and minimizes the cell count required to extend the domain to the outer edges where free stream boundary conditions can be applied.","order":33,"static_url":"/research/38/"},{"section":"Research","title":"Aircraft airframe noise: Noise control of landing gear using pereforated fairings","url":"/research/39/","summary":"Landing gear noise can be the dominant component of airframe noise, especially for larger aircraft. The interaction of the airflow with protrusions and cavities gives rise to unsteady flow phenomena constituting a potent sound generating mechanism. Shielding landing gear compone…","meta":"Aeroacoustics","search_text":"aircraft airframe noise: noise control of landing gear using pereforated fairings landing gear noise can be the dominant component of airframe noise, especially for larger aircraft. the interaction of the airflow with protrusions and cavities gives rise to unsteady flow phenomena constituting a potent sound generating mechanism. shielding landing gear components with fairings and thereby preventing this interaction has been considered before. high speed flow deflection onto other components and fairing self-noise are disadvantages of these fairings. bleeding air through the fairings by making them porous can reduce the impact of these effects and result in a noise reduction. aeroacoustics landing gear noise can be the dominant component of airframe noise, especially for larger aircraft. the interaction of the airflow with protrusions and cavities gives rise to unsteady flow phenomena constituting a potent sound generating mechanism. shielding landing gear components with fairings and thereby preventing this interaction has been considered before. high speed flow deflection onto other components and fairing self-noise are disadvantages of these fairings. bleeding air through the fairings by making them porous can reduce the impact of these effects and result in a noise reduction.","order":34,"static_url":"/research/39/"},{"section":"Research","title":"Aircraft airframe noise: Large-eddy simulation of jet interaction with a wing","url":"/research/40/","summary":"Jet engines and airframes are the two main contributors to aircraft noise, with the latter including both high-lift devices and landing gears. To achieve reductions in aircraft noise, it is necessary to reduce the noise from all components that contribute significantly to the to…","meta":"Aeroacoustics","search_text":"aircraft airframe noise: large-eddy simulation of jet interaction with a wing jet engines and airframes are the two main contributors to aircraft noise, with the latter including both high-lift devices and landing gears. to achieve reductions in aircraft noise, it is necessary to reduce the noise from all components that contribute significantly to the total noise and noise due to the interactions between components. aeroacoustics jet engines and airframes are the two main contributors to aircraft noise, with the latter including both high-lift devices and landing gears. to achieve reductions in aircraft noise, it is necessary to reduce the noise from all components that contribute significantly to the total noise and noise due to the interactions between components. noise generation by the vortical flow from jet engine interacting with airframe structures, such as high-left devices when the wing is at landing configuration with flap deployed, is a fundamental problem affecting the design and performance of an aircraft and its system. understanding of the installation effect would help to design more efficient and more environmentally friendly aircraft. the main objectives for this study were to: 1. investigate aerodynamic noise due to the interaction of the vortical flow from a jet engine with high-lift devices; 2. perform les for the turbulent flow around wings, with and without the influence from the jet. understand flow physics and noise generation mechanisms for the phenomenon of jet wing interaction; 3. investigate the radiated noise to far field due to jet-wing interaction using the fw-h method for sound wave propagation, to compare predicted far veld noise with experimental data.","order":35,"static_url":"/research/40/"},{"section":"Research","title":"Aircraft airframe noise: Slat noise attenuation with acoustic liner treatment","url":"/research/41/","summary":"The significant contribution of the flows around the leading edge slat on the wing of a commercial aircraft to the airframe noise during approach and landing motivates this research project to identify the mechanisms of leading edge slat noise and passively control these acousti…","meta":"Aeroacoustics","search_text":"aircraft airframe noise: slat noise attenuation with acoustic liner treatment the significant contribution of the flows around the leading edge slat on the wing of a commercial aircraft to the airframe noise during approach and landing motivates this research project to identify the mechanisms of leading edge slat noise and passively control these acoustic sources. aeroacoustics the significant contribution of the flows around the leading edge slat on the wing of a commercial aircraft to the airframe noise during approach and landing motivates this research project to identify the mechanisms of leading edge slat noise and passively control these acoustic sources. several flow phenomena take place due to the separated flow in the slat cove region and its interaction with the surrounding flow such as, low-speed recirculation flow, free shear layer, and ejections of large-scale structures merging with the slat wake. other important phenomena can also exist, such as, the interaction of the slat wake with the wing boundary layer, referred to as the confluent boundary layer, and slat trailing edge vortex shedding. all of these may cause the noise generation. to understand the physics and mechanisms behind these phenomena and to find a way to reduce the slat noise, accurate simulations of the complex unsteadiness flow of the high-lift wing are needed. to develop and apply computational aeroacoustic methods using the sotoncaa code to reveal the mechanism of the slat noise generation and demonstrate the feasibility of controlling the slat noise using acoustic liners.","order":36,"static_url":"/research/41/"},{"section":"Research","title":"Aircraft airframe noise: Investigation of aircraft noise in steep approach","url":"/research/42/","summary":"Airframe noise has been found to be the dominant source of noise for an aircraft on approach to landing. Airframe noise is made up of the HLD noise and landing gear noise. In order to reduce noise on the ground steep approach landing procedures can be used.","meta":"Aeroacoustics","search_text":"aircraft airframe noise: investigation of aircraft noise in steep approach airframe noise has been found to be the dominant source of noise for an aircraft on approach to landing. airframe noise is made up of the hld noise and landing gear noise. in order to reduce noise on the ground steep approach landing procedures can be used. aeroacoustics airframe noise has been found to be the dominant source of noise for an aircraft on approach to landing. airframe noise is made up of the hld noise and landing gear noise. in order to reduce noise on the ground steep approach landing procedures can be used. figure 1 shows a typical steep approach trajectory. steep approach utilises a steeper glide slope than the conventional -3 deg glide slope. as a result the aircraft flies at a higher altitudes over residential areas close to the airport. increasing distance to the ground reduces the noise on the ground significantly according to the inverse square law. in order to meet the decent velocity requirement for landing, spoilers are used as air brakes to slow down the aircraft. the aim is to understand the underlying flow dynamics of noise generation on a hld with deflected spoilers in steep approach landing configuration. based on the results we aim to develop noise reduction techniques that can be applied to the hld configuration to reduce the noise impact due to deflected spoilers. a high-order time accurate aeroacoustics code sotoncaa is being used to perform the simulations.","order":37,"static_url":"/research/42/"},{"section":"Research","title":"Aircraft airframe noise: Blowing for bluff-body noise control","url":"/research/43/","summary":"Landing gear noise is a major contributor to airframe noise. Wakes from upstream components impinging on downstream components are a significant source of noise. This work investigates the use of flow control to reduce the noise generated by bluff bodies.","meta":"Aeroacoustics","search_text":"aircraft airframe noise: blowing for bluff-body noise control landing gear noise is a major contributor to airframe noise. wakes from upstream components impinging on downstream components are a significant source of noise. this work investigates the use of flow control to reduce the noise generated by bluff bodies. aeroacoustics landing gear noise is a major contributor to airframe noise. wakes from upstream components impinging on downstream components are a significant source of noise. this work investigates the use of flow control to reduce the noise generated by bluff bodies. after the bluff body demonstration case the flow control was applied to an aircraft main landing gear. the aim of this work was to assess and develop local blowing flow control methods for bluff body noise reduction. the first demonstration case was on isolated components, i.e., a cylinder and an h-beam. a tandem configuration of an h-beam and a cylinder was used to investigate interaction noise between two bluff bodies. for the isolated components a pneumatic split plate was investigated. a small jet was applied on the rearward face 180 deg. from the stagnation line of two bluff bodies to provide an analogous reduction in bluff body noise to that achieved with a physical split plate. for the interaction case the flow control was applied to the cylinder to break down the large flow structures and to displace the peak turbulence away from the surface of the downstream component.","order":38,"static_url":"/research/43/"},{"section":"Research","title":"Aircraft Engine Studies: Modelling next generation CROR aircraft","url":"/research/45/","summary":"Contra-rotating open rotors (CRORs) show promise for use in future aircraft propulsion systems, but suffer from high noise emissions. Both tonal and broadband noise emissions are produced by CRORs.","meta":"Aeroacoustics","search_text":"aircraft engine studies: modelling next generation cror aircraft contra-rotating open rotors (crors) show promise for use in future aircraft propulsion systems, but suffer from high noise emissions. both tonal and broadband noise emissions are produced by crors. aeroacoustics contra-rotating open rotors (crors) show promise for use in future aircraft propulsion systems, but suffer from high noise emissions. both tonal and broadband noise emissions are produced by crors. historically, tonal noise has been more extensively studied because it was thought to be the dominant noise type. however, recent studies have shown that broadband noise is also significant. therefore, research is needed to better understand the generation of cror broadband noise. the project concentrates on two areas of cror broadband noise. firstly, analytic models are being developed to improve industrial modelling of the noise. secondly, the assumptions which are made in the analytic models are being tested with the use of high-order computational aeroacoustic (caa) methods.","order":39,"static_url":"/research/45/"},{"section":"Research","title":"Aircraft Engine Studies: Development of a whole-aicraft noise model","url":"/research/46/","summary":"We develop an advanced computer program to estimate aircraft noise, both far-field radiation and scattering on fuselage.","meta":"Aeroacoustics","search_text":"aircraft engine studies: development of a whole-aicraft noise model we develop an advanced computer program to estimate aircraft noise, both far-field radiation and scattering on fuselage. aeroacoustics we develop an advanced computer program to estimate aircraft noise, both far-field radiation and scattering on fuselage. the program can calculate noise scattering using workstation efficient and accurately. the code allows integration of different kinds of noise sources, such as, propeller noise, jet noise and airframe noise. the method is in frequency domain; but due to its short execution time, it has the potential to be applied for broadband noise. with its low computation costs and flexibility for integrating different noise sources, this model has the potential to be a useful engineering tool on noise analysis and relative design optimisation.","order":40,"static_url":"/research/46/"},{"section":"Research","title":"Aircraft Engine Studies: Efficient computation of sound radiation on adaptively refined mesh","url":"/research/47/","summary":"A new computational tool was developed to efficiently predict sound radiation with block-structured adaptive mesh refinement (AMR) algorithm.","meta":"Aeroacoustics","search_text":"aircraft engine studies: efficient computation of sound radiation on adaptively refined mesh a new computational tool was developed to efficiently predict sound radiation with block-structured adaptive mesh refinement (amr) algorithm. aeroacoustics a new computational tool was developed to efficiently predict sound radiation with block-structured adaptive mesh refinement (amr) algorithm. the basic idea was to use grids of fine resolution only for the area where sound propagates. as a result the required grid number is reduced and the computational efficiency can be increased. the work includes parallel implementation of the amr algorithm, a high-order solver, and linear models for acoustics. practical problems, such as spinning modal radiation from an aero engine duct, were studied with the tool. compared to the computation performed on a fixed mesh, the computational efficiency by the amr method is increased extensively while the accuracy of the solution is still maintained.","order":41,"static_url":"/research/47/"},{"section":"Research","title":"Aircraft Engine Studies: Modelling of aircraft sound propagation","url":"/research/48/","summary":"A suite of high-order, time-domain computational aeroacoustic programs have been developed to model sound propagation and radiation from airframe components and aero engine intake and bypass/exhaust ducts.","meta":"Aeroacoustics","search_text":"aircraft engine studies: modelling of aircraft sound propagation a suite of high-order, time-domain computational aeroacoustic programs have been developed to model sound propagation and radiation from airframe components and aero engine intake and bypass/exhaust ducts. aeroacoustics a suite of high-order, time-domain computational aeroacoustic programs have been developed to model sound propagation and radiation from airframe components and aero engine intake and bypass/exhaust ducts. the method is based on multi-block, structured grids and high-order compact schemes and is capable of modelling the effect of liner, bifurcation, etc. simulations have been performed of noise propagation/radiation problems associated with high lift devices (hlds), e.g. slats, flaps, spoilers, and both engine intake and bypass ducts. new features are being implemented including efficient computation of broadband noise content for engine applications. new formulations of linearised euler and acoustic perturbation equations are also being developed.","order":42,"static_url":"/research/48/"},{"section":"Research","title":"Stable time-domain LEE simulations","url":"/research/28/","summary":"Linearized Euler equations (LEE) are often used in a CAA simulation, with a strong mean-velocity gradient, numerical Kelvin-Helmholtz (K-H) instabilities may appear using the LEE. Vortical instabilities can grow exponentially and contaminate the solution.","meta":"Aeroacoustics","search_text":"stable time-domain lee simulations linearized euler equations (lee) are often used in a caa simulation, with a strong mean-velocity gradient, numerical kelvin-helmholtz (k-h) instabilities may appear using the lee. vortical instabilities can grow exponentially and contaminate the solution. aeroacoustics to developing new instability suppression methods and compare the accuracy and computation cost of the proposed methods with previous methods. in this case, a time-harmonic acoustic wave propagates across a 2- d domain, and the sound is refracted across a finite shear layer. the solution field obtained the lee is clearly contaminated by the numerical instability, while the proposed adt method can an untouched acoustic filed. in this case, a time-harmonic acoustic wave propagates across a 2- d domain, and the sound is refracted across a finite shear layer. comparing with the lee solution, where the k-h instabilities appears and large spurious wave can be observed, the proposed method can provide uncontaminated results in acoustics near field and far field. yuhao sun and ryu fattah","order":43,"static_url":"/research/28/"},{"section":"Research","title":"Anisotropic filter for synthetic turbulence","url":"/research/27/","summary":"A technique of synthetic turbulence is proposed by developing a general form of anisotropic filter, which can realize the desired velocity spectra of three-dimensional anisotropic turbulence. The anisotropic filter can be directly implemented instead of obtaining the non-Gaussia…","meta":"Aeroacoustics","search_text":"anisotropic filter for synthetic turbulence a technique of synthetic turbulence is proposed by developing a general form of anisotropic filter, which can realize the desired velocity spectra of three-dimensional anisotropic turbulence. the anisotropic filter can be directly implemented instead of obtaining the non-gaussian energy spectra through gaussian superposition, which is then combined with linearised euler equations to predict the leading edge noise. aeroacoustics to develop a new method of synthetic anisotropic turbulence by deriving a general form of anisotropic filter that generates the homogeneous anisotropic turbulence. to investigate the influence of anisotropy on turbulence-airfoil interaction noise by applying various stretching ratios. the effectiveness of pseudo three-dimensional anisotropic filter is verified by comparing with amiet’s analytical solution. the turbulent velocity field induced by the anisotropic filters can be regarded as the pseudo three-dimensional anisotropic turbulence, which will reproduce the major statistics of three-dimensional turbulence through an integral solution of the three-dimensional fw-h equation, the far-field spl spectra is obtained, which shows good agreement with the theoretical solution, to within 1.5 db accuracy. it can be concluded that doubling of the tangential turbulent length scale leads to 9 db increase in spl spectra, which is attributed to the octupling of one-dimensional energy in the transverse direction. zhen shen synthesized anisotropic and three-dimensional turbulence validation of the anisotropic filter using analytical solutions. validation of the anisotropic filter using analytical solutions.","order":44,"static_url":"/research/27/"},{"section":"Research","title":"The Aeroacoustic Characteristics of a Heaving Airfoil","url":"/research/24/","summary":"Airfoil oscillation is a widely observed phenomenon in real applications, such as natural flyers, helicopter and drone blades, etc. This work studies the aeroacoustic characteristics of a heaving airfoil by experimental methods","meta":"Aeroacoustics","search_text":"the aeroacoustic characteristics of a heaving airfoil airfoil oscillation is a widely observed phenomenon in real applications, such as natural flyers, helicopter and drone blades, etc. this work studies the aeroacoustic characteristics of a heaving airfoil by experimental methods aeroacoustics airfoil oscillation is a widely observed phenomenon in real applications, such as natural flyers, helicopter and drone blades, etc. the instantaneous flow pattern on a pitching airfoil is acquired by a high-speed piv system. all measurements were conducted in the low-speed open-jet facility in the hong kong university of science and technology. the tunnel outlet has a dimension of 0.4m × 0.4m, and the largest wind speed of 70m/s. a straight wing model with the profile naca 0012 was tested, and it had a 100mm chord and 399mm span. the heaving motion was actuated by a voice coil motor. the far-field noise was measured by three microphones placed along an arc centered at the trailing edge of the airfoil a comparison of the noise spectra between the stationary and heaving cases at flow speeds of 10m/s and 40m/s are given in the figures below, respectively. the following observations can be obtained: 1. the heaving motion suppresses the height of the primary tone and enhances the secondary peaks 2. when the flow speed is 10m/s, a broadband hump in the vicinity to the primary tone raises due to the heaving motion. teng zhou and yuhao sun figure 1: the setup of the experiment. comparison of the time-frequency analysis between the static and heaving cases. : comparisons of the spectra obtained under the static and heaving conditions.","order":45,"static_url":"/research/24/"},{"section":"Research","title":"Non-Reflective Boundary Conditions for CAA","url":"/research/22/","summary":"Non-reflective boundary conditions are essential for accurate computational aeroacoustic (CAA) simulations. Benchmark test cases were developed to quantify the reflections generated by outgoing acoustic and vortical disturbances. These test cases were used to develop a new blend…","meta":"Aeroacoustics","search_text":"non-reflective boundary conditions for caa non-reflective boundary conditions are essential for accurate computational aeroacoustic (caa) simulations. benchmark test cases were developed to quantify the reflections generated by outgoing acoustic and vortical disturbances. these test cases were used to develop a new blended zonal characteristic boundary condition (cbc) with optimized parameters to maximise the solution accuracy. aeroacoustics a zonal characteristic boundary condition was developed from two benchmark test cases. the acoustic plane wave tests accurately quantify the reflections generated a boundary condition across a range of mach number, wave angle, and streamwise and transverse wave numbers. the other benchmark test case used synthetic turbulence to model the vorticity disturbances. several tests were conducted to evaluate the performance of various methods. the free parameters in the zonal characteristic method were optimized to minimize the acoustic reflections for both acoustic and vortical cases. the final result is a near-perfect non-reflective boundary condition. finally, the optimal methods from both benchmark cases were blended into a generalized formula a zonal characteristic boundary condition was developed from two benchmark test cases. the acoustic plane wave tests accurately quantify the reflections generated a boundary condition across a range of mach number, wave angle, and streamwise and transverse wave numbers. the other benchmark test case used synthetic turbulence to model the vorticity disturbances. several tests were conducted to evaluate the performance of various methods. the free parameters in the zonal characteristic method were optimized to minimize the acoustic reflections for both acoustic and vortical cases. the final result is a near-perfect non-reflective boundary condition. finally, the optimal methods from both benchmark cases were blended into a generalized formulation that automatically switches depending on the local vorticity magnitude. ryu fattah and james gill with non-reflective boundary conditions withoutr non-reflective boundary conditions incident plane wave","order":46,"static_url":"/research/22/"},{"section":"Facilities & software","title":"Navier-Stokes Solver","url":"/facility/32/","summary":"High-order CAA and low-order CFD codes are used by the research group to study the complex flow fields around streamlined and bluff bodies. The high-order solver employs the same numerical schemes and non-reflective boundary conditions that are used in the LEE and Euler solvers.…","meta":"Computational aeroacoustics and software","search_text":"navier-stokes solver high-order caa and low-order cfd codes are used by the research group to study the complex flow fields around streamlined and bluff bodies. the high-order solver employs the same numerical schemes and non-reflective boundary conditions that are used in the lee and euler solvers. a hybrid rans/les strategy is typically applied to complex geometries to resolve the wide range of flow structures that are critical to the radiated noise level. in some cases, we employ a low-order open-source cfd code, which was used to develop the video. in the video, the complex flow structures around an aircraft nose landing gear are illustrated. computational aeroacoustics and software","order":47,"static_url":"/facility/32/"},{"section":"Facilities & software","title":"Advanced synthetic turbulence methods","url":"/facility/31/","summary":"Synthetic turbulence methods are developed in AANTC to reproduce turbulence with specific turbulence spectra. A new method of synthetic anisotropic turbulence by deriving a general form of anisotropic filter that generates the homogeneous anisotropic turbulence. To investigate t…","meta":"Computational aeroacoustics and software","search_text":"advanced synthetic turbulence methods synthetic turbulence methods are developed in aantc to reproduce turbulence with specific turbulence spectra. a new method of synthetic anisotropic turbulence by deriving a general form of anisotropic filter that generates the homogeneous anisotropic turbulence. to investigate the influence of anisotropy on turbulence-airfoil interaction noise by applying various stretching ratios. ref. zhen shen, xin zhang, direct anisotropic filter method of generating synthetic turbulence applied to turbulence-airfoil interaction noise prediction, journal of sound and vibration, vol. 458, pp. 544-564, 2019. computational aeroacoustics and software","order":48,"static_url":"/facility/31/"},{"section":"Facilities & software","title":"Efficient boundary element method","url":"/facility/30/","summary":"An efficient boundary element method (BEM) solver has been developed at AANTC to compute the sound scattering from the objects, which can be acoustical hard or impedance walls. Reduced order modelling technologies are employed to improve the computational efficiency, and special…","meta":"Computational aeroacoustics and software","search_text":"efficient boundary element method an efficient boundary element method (bem) solver has been developed at aantc to compute the sound scattering from the objects, which can be acoustical hard or impedance walls. reduced order modelling technologies are employed to improve the computational efficiency, and special treatments are conducted to remove the unphysical instability modes. the solver has been applied to drone fuselage scattering and acoustic window performance estimation. ref. hanbo jiang, et al., boundary element analysis on fuselage scattering of drone noise, international journal of aeroacoustics, pp. 1-14, 2022. computational aeroacoustics and software","order":49,"static_url":"/facility/30/"},{"section":"Facilities & software","title":"Rotor noise prediction methods","url":"/facility/29/","summary":"A rotor noise prediction method based on the Hanson model was developed to compute the tonal noise of rotors. The effects of unsteady modes on the noise radiation are considered. Also, the broadband noise is computed using the empirical models of trailing edge noise. The rotatio…","meta":"Computational aeroacoustics and software","search_text":"rotor noise prediction methods a rotor noise prediction method based on the hanson model was developed to compute the tonal noise of rotors. the effects of unsteady modes on the noise radiation are considered. also, the broadband noise is computed using the empirical models of trailing edge noise. the rotation effects are accounted for in the prediction models. the aerodynamic variables are estimated using a cost-effective blade element and moment theory solver. the prediction results match well with the experiments. ref: siyang zhong, et al., a revisit of the tonal noise of small rotors, proceedings of the royal society a., vol. 476, pp. 20200491, 2020. computational aeroacoustics and software","order":50,"static_url":"/facility/29/"},{"section":"Facilities & software","title":"Acoustic preserved artificial compressibility (APAC) method","url":"/facility/28/","summary":"In AANTC, an acoustic preserved artificial compressibility method is developed to compute the sound generation and propagation at low Mach numbers. It can account for the compressibility, which is related to the sound generation process, at equivalent computational cost with the…","meta":"Computational aeroacoustics and software","search_text":"acoustic preserved artificial compressibility (apac) method in aantc, an acoustic preserved artificial compressibility method is developed to compute the sound generation and propagation at low mach numbers. it can account for the compressibility, which is related to the sound generation process, at equivalent computational cost with the incompressible solvers. it efficiently models the noise from rotors and flying vehicles. ref. hanbo jiang, xin zhang, “an acoustic-wave preserved artificial compressibility method for low-mach number aeroacoustic simulations”, journal of sound and vibration, vol. 516, 116505, 2022. computational aeroacoustics and software","order":51,"static_url":"/facility/28/"},{"section":"Facilities & software","title":"An environmental noise assessment code based on Gaussian beam tracing","url":"/facility/27/","summary":"An environmental noise assessment EnvARC is developed in AANTC to study the noise impact on the urban environment. It is based on a Gaussian beam tracing method. Different source models can be introduced as input, and the city model can be input from the geographic information s…","meta":"Computational aeroacoustics and software","search_text":"an environmental noise assessment code based on gaussian beam tracing an environmental noise assessment envarc is developed in aantc to study the noise impact on the urban environment. it is based on a gaussian beam tracing method. different source models can be introduced as input, and the city model can be input from the geographic information system. the effect of atmospheric condition and acoustic features on the geometric surface are introduced. ref. haoyu bian, et al., an efficient rectilinear gaussian beam tracing method for sound propagation modelling in a non-turbulent medium, journal of acoustical society of america, vol. 148, pp. 4037-4048, 2020. computational aeroacoustics and software","order":52,"static_url":"/facility/27/"},{"section":"Facilities & software","title":"Rotor noise test platform","url":"/facility/26/","summary":"A rotor aerodynamic and aeroacoustic measurement platform is developed in AANTC to study rotor aerodynamics and aeroacoustics. The rotor locations are accurately controlled by a high-resolution 2D transverse, and the 20 microphones are used to measure the noise properties. The a…","meta":"Experimental aerodynamics","search_text":"rotor noise test platform a rotor aerodynamic and aeroacoustic measurement platform is developed in aantc to study rotor aerodynamics and aeroacoustics. the rotor locations are accurately controlled by a high-resolution 2d transverse, and the 20 microphones are used to measure the noise properties. the aerodynamic forces are measured using high-accuracy load cells. ref: han wu et al., a rotor blade aeroacoustics test platform at hkust, internoise 2020, vol. 261, pp. 2476-2484, 2020. experimental aerodynamics","order":53,"static_url":"/facility/26/"},{"section":"Facilities & software","title":"Airfoil noise measurement platform","url":"/facility/25/","summary":"An airfoil noise measurement platform is developed in AANTC based on the anechoic wind tunnel. A microphone array with 56 microphone is used for sound source detection. The diameter is 0.7m and the frequency range is 50-10000 Hz. A laser profiler is used to measure the deformati…","meta":"Experimental aerodynamics","search_text":"airfoil noise measurement platform an airfoil noise measurement platform is developed in aantc based on the anechoic wind tunnel. a microphone array with 56 microphone is used for sound source detection. the diameter is 0.7m and the frequency range is 50-10000 hz. a laser profiler is used to measure the deformation of flexible airfoils. ref: peng zhou, siyang zhong, xin zhang, on the effect of velvet structures on trailing edge noise: experimental investigation and theoretical analysis, journal of fluid mechanics, vol. 919, a11, 2021 experimental aerodynamics","order":54,"static_url":"/facility/25/"},{"section":"Facilities & software","title":"Phased Microphone Array","url":"/facility/24/","summary":"Phased microphone array is used in AANTC to detect the aerodynamic sound sources. The array contains 56 Brüel & Kjær microphones and different beamforming algorithms are available for data processing.","meta":"Experimental aerodynamics","search_text":"phased microphone array phased microphone array is used in aantc to detect the aerodynamic sound sources. the array contains 56 brüel & kjær microphones and different beamforming algorithms are available for data processing. experimental aerodynamics","order":55,"static_url":"/facility/24/"},{"section":"Facilities & software","title":"Spinning mode duct test rig","url":"/facility/23/","summary":"A duct mode detection facility is developed in AANTC to evaluate the noise reduction in engine ducts. It is also used for duct mode detection method. The rig has a diameter of 200 mm, the flow speed is 10-60m/s, and the maximum working frequency is 8000 Hz. More details: H. Bu, …","meta":"Experimental aerodynamics","search_text":"spinning mode duct test rig a duct mode detection facility is developed in aantc to evaluate the noise reduction in engine ducts. it is also used for duct mode detection method. the rig has a diameter of 200 mm, the flow speed is 10-60m/s, and the maximum working frequency is 8000 hz. more details: h. bu, x. huang, x. zhang, an overview of testing methods for aeroengine fan noise, progress in aerospace sciences, vol. 124, 100722, 2021. experimental aerodynamics","order":56,"static_url":"/facility/23/"},{"section":"Facilities & software","title":"Impedance tubes","url":"/facility/22/","summary":"Different impedance tubes are used to measure the acoustic impedance of sound absorption materials. It can characterize the sound transmission loss and surface impedance as well. The working frequencies of the commercial Brüel & Kjær Type 4206 impedance tube are 50-1600 Hz (with…","meta":"Experimental aerodynamics","search_text":"impedance tubes different impedance tubes are used to measure the acoustic impedance of sound absorption materials. it can characterize the sound transmission loss and surface impedance as well. the working frequencies of the commercial brüel & kjær type 4206 impedance tube are 50-1600 hz (with diameter of 100 mm) and 500-6400 hz (with diameter of 29 mm), respectively. a fabricated impedance tube has square cross-section of 50x50 mm, and the working frequency range is 500-3430 hz. experimental aerodynamics","order":57,"static_url":"/facility/22/"},{"section":"Facilities & software","title":"Grazing flow tube","url":"/facility/21/","summary":"There are two flow tube facilities in AANTC to study the effects of grazing flows on acoustic liners. Impedance eduction methods are conducted for different types of sound absorption materials. The dimensions of tubes are 50x50 mm and the working frequency is 400-3400 Hz. The ma…","meta":"Experimental aerodynamics","search_text":"grazing flow tube there are two flow tube facilities in aantc to study the effects of grazing flows on acoustic liners. impedance eduction methods are conducted for different types of sound absorption materials. the dimensions of tubes are 50x50 mm and the working frequency is 400-3400 hz. the maximum mach and sound pressure levels for a are 0.1 and 120 db, respectively. the test rig is upgraded to enable wide test range. the mach number ad spl limits are 0.3 and 140 db, respectively. more details: wei yi, et al., acoustic impedance measurements using an advanced grazing flow tube facility, 28th international congress on sound and vibration, 2022. experimental aerodynamics grazing flow tube grazing flow tube","order":58,"static_url":"/facility/21/"},{"section":"Facilities & software","title":"Low Noise Low Speed Wind tunnel facility","url":"/facility/20/","summary":"The low-noise low-speed wind tunnel contains two test sections. Both sections have a cross-section of about 2.5 m wide and 2 m high and the test wind speed ranges from 15 m/s to 40 m/s. In aerodynamic test section, a model support is designed for studying the wind loading on air…","meta":"Experimental aerodynamics","search_text":"low noise low speed wind tunnel facility the low-noise low-speed wind tunnel contains two test sections. both sections have a cross-section of about 2.5 m wide and 2 m high and the test wind speed ranges from 15 m/s to 40 m/s. in aerodynamic test section, a model support is designed for studying the wind loading on aircraft model, uav, propeller model, etc. the support is capable of changing the pitch, yaw and roll angle of model. the flow at the aerodynamic test section is a uniform smooth flow with turbulence less than 0.12%. in structural/environmental test section, it is typically used for detailed model tests, such as high frequency force balance tests, pressure tests and pedestrian level wind environment. the test section has a fetch length of 6 m and is fitted with 93 computer controlled, pneumatically operated roughness elements that allow fine control of the simulated turbulence characteristics. more details: https://aaf.ust.hk/fac/1/ experimental aerodynamics","order":59,"static_url":"/facility/20/"},{"section":"Facilities & software","title":"Anechoic wind tunnel","url":"/facility/11/","summary":"he anechoic wind tunnel houses an open-jet inflow duct of 0.4m (W) by 0.4m(H), and an outlet that has a cross-section of 0.6m (W) by 0.6m (H). The test section is enclosed within an anechoic chamber that has dimensions of 3.3m(L) x 3.1m(W) x 2.0m(H). The wind tunnel speed ranges…","meta":"Experimental aerodynamics","search_text":"anechoic wind tunnel he anechoic wind tunnel houses an open-jet inflow duct of 0.4m (w) by 0.4m(h), and an outlet that has a cross-section of 0.6m (w) by 0.6m (h). the test section is enclosed within an anechoic chamber that has dimensions of 3.3m(l) x 3.1m(w) x 2.0m(h). the wind tunnel speed ranges from 10m/s to 70m/s. more details: yi et al., design and characterization of a multifunctional low-speed anechoic wind tunnel at hkust, aerospace science and technology, vol. 115, pp. 106814, 2021. experimental aerodynamics anechoic wind tunnel","order":60,"static_url":"/facility/11/"},{"section":"Facilities & software","title":"Linearised Euler solver","url":"/facility/15/","summary":"We use a high-order Linearised Euler Equation (LEE) solver to study specific aeroacoustic problems that are not governed by nonlinear and viscous effects. An LEE solver is significantly faster than a Navier-Stokes solver, and it has been used to understand how sound propagates i…","meta":"Computational aeroacoustics and software","search_text":"linearised euler solver we use a high-order linearised euler equation (lee) solver to study specific aeroacoustic problems that are not governed by nonlinear and viscous effects. an lee solver is significantly faster than a navier-stokes solver, and it has been used to understand how sound propagates in complex environments. in the video, the lee solver illustrates how sound generated inside an aircraft engine propagates towards the bypass outlet and scatters around the engine walls. high-order numerical schemes and non-reflective boundary conditions are applied to minimise the numerical error and to maximise the computational efficiency. computational aeroacoustics and software linearised euler solver","order":61,"static_url":"/facility/15/"},{"section":"Facilities & software","title":"Euler solver with shock capturing","url":"/facility/16/","summary":"We use a high-order Euler solver to study aeroacoustic problems that have nonlinear physics. In the video, the Euler solver shows what happens when a turbulent field impinges on the leading edge of a transonic aerofoil. This kind of problem is relevant for aircraft engine compon…","meta":"Computational aeroacoustics and software","search_text":"euler solver with shock capturing we use a high-order euler solver to study aeroacoustic problems that have nonlinear physics. in the video, the euler solver shows what happens when a turbulent field impinges on the leading edge of a transonic aerofoil. this kind of problem is relevant for aircraft engine components that operate at high speeds and that are subjected to oncoming flow disturbances. a shock-wave formed near the mid-chord of the aerofoil interacts strongly with the incoming turbulent field (shown in the bottom right corner of the video). the resulting noise radiated from the leading edge and the shock-wave is illustrated in the video. the solver employs high-order numerical schemes and non-reflective boundary conditions, together with a local artificial diffusivity model for the shock capturing. computational aeroacoustics and software euler solver with shock capturing","order":62,"static_url":"/facility/16/"},{"section":"Facilities & software","title":"2D Acoustic plane wave test rig","url":"/facility/12/","summary":"This facility was designed and fabricated at HKUST, and it is used to evaluate prototype acoustic materials. Test samples are sandwiched tightly between two paralleled Plexi glass plates (2.4 m x 1.2 m x 0.02 m), which provide a two-dimensional (2D) waveguide environment below 5…","meta":"Experimental aerodynamics","search_text":"2d acoustic plane wave test rig this facility was designed and fabricated at hkust, and it is used to evaluate prototype acoustic materials. test samples are sandwiched tightly between two paralleled plexi glass plates (2.4 m x 1.2 m x 0.02 m), which provide a two-dimensional (2d) waveguide environment below 5700 hz. foam wedges are applied along the sides of the test region to ensure an anechoic environment. the incident sound field is generated by an array of twenty pui audio as04008cor loud speakers, and it is measured by a g.r.a.s type 46be microphone. another g.r.a.s microphone is used to measure the transmitted/refracted sound field. the microphones are mounted onto a parker hannifin 2d traverse system which allows the entire incident and transmitted/refracted sound field to be studied. more details: yi fang et al, sound transmission through an acoustic porous metasurface with periodic structures, applied physics letter, vol. 110, 171904, 2017. experimental aerodynamics 2d acoustic plane wave test rig","order":63,"static_url":"/facility/12/"},{"section":"Facilities & software","title":"Large aerodynamic wind tunnel","url":"/facility/14/","summary":"WWTF's wind tunnel contains two test sections that are specifically designed for aerospace engineering and structural/environmental engineering. Both sections have a cross-section of about 2.5 m wide and 2 m high and the test wind speed ranges from 15 m/s to 40 m/s. In aerodynam…","meta":"Experimental aerodynamics","search_text":"large aerodynamic wind tunnel wwtf's wind tunnel contains two test sections that are specifically designed for aerospace engineering and structural/environmental engineering. both sections have a cross-section of about 2.5 m wide and 2 m high and the test wind speed ranges from 15 m/s to 40 m/s. in aerodynamic test section, a model support is designed for studying the wind loading on aircraft model, uav, propeller model, etc. the support is capable of changing the pitch, yaw and roll angle of model. the flow at the aerodynamic test section is a uniform smooth flow with turbulence less than 0.12%. in structural/environmental test section, it is typically used for detailed model tests, such as high frequency force balance tests, fa癟ade pressure tests and pedestrian level wind environment. the test section has a fetch length of 6 m and is fitted with 93 computer controlled, pneumatically operated roughness elements that allow fine control of the simulated turbulence characteristics. experimental aerodynamics large aerodynamic wind tunnel","order":64,"static_url":"/facility/14/"},{"section":"Facilities & software","title":"B&K Type 4206 Four-microphone Impedance Measurement Tube","url":"/facility/13/","summary":"This device is used to characterise the impedance and transmission loss properties of materials, in the frequency range of 50Hz-6.4kHz. Material samples with a diameter of 29mm and 100mm can be evaluated in the frequency range of 500Hz-6.4kHz and 50Hz-1.6kHz, respectively. The a…","meta":"Experimental aerodynamics","search_text":"b&k type 4206 four-microphone impedance measurement tube this device is used to characterise the impedance and transmission loss properties of materials, in the frequency range of 50hz-6.4khz. material samples with a diameter of 29mm and 100mm can be evaluated in the frequency range of 500hz-6.4khz and 50hz-1.6khz, respectively. the acoustic impedance and admittance are measured with this device. the sound absorption, reflection, and transmission loss coefficients are also obtained from this system. experimental aerodynamics four-microphone impedance measurement tube","order":65,"static_url":"/facility/13/"},{"section":"Facilities & software","title":"Performance Sports Test Rig","url":"/facility/18/","summary":"The experimental test is conducted in the wind tunnel in combination with the test rig. The wind tunnel is exclusively designed for speed racing purpose with low turbulence intensity and steady dynamic pressure. The test rig is a platform consists of 6-component balance, motor, …","meta":"Experimental aerodynamics","search_text":"performance sports test rig the experimental test is conducted in the wind tunnel in combination with the test rig. the wind tunnel is exclusively designed for speed racing purpose with low turbulence intensity and steady dynamic pressure. the test rig is a platform consists of 6-component balance, motor, cadence and torque sensor. the experiment facility can be applied in the measurement of full-scale cycling drag, the cloth drag test, yaw angle effect, etc. experimental aerodynamics performance sports test rig","order":66,"static_url":"/facility/18/"},{"section":"Facilities & software","title":"Sound extrapolation method for turbulent flows","url":"/facility/19/","summary":"In aeroacoustics, the far-field directivity is often computed using the integral solution of the acoustic analogy equations. The sound prediction prediction can be rendered when the turbulent eddies move across the integration surface, and the expensive volume integral terms are…","meta":"Computational aeroacoustics and software","search_text":"sound extrapolation method for turbulent flows in aeroacoustics, the far-field directivity is often computed using the integral solution of the acoustic analogy equations. the sound prediction prediction can be rendered when the turbulent eddies move across the integration surface, and the expensive volume integral terms are neglected. computational aeroacoustics and software sound extrapolation method for turbulent flows","order":67,"static_url":"/facility/19/"},{"section":"Facilities & software","title":"Acoustic Plane Wave Test Rig","url":"/facility/8/","summary":"This facility was designed and fabricated at HKUST, and it is used to evaluate prototype acoustic materials. Test samples are sandwiched tightly between two paralleled Plexi glass plates (2.4 m x 1.2 m x 0.02 m), which provide a two-dimensional (2D) waveguide environment below 5…","meta":"Experimental aerodynamics","search_text":"acoustic plane wave test rig this facility was designed and fabricated at hkust, and it is used to evaluate prototype acoustic materials. test samples are sandwiched tightly between two paralleled plexi glass plates (2.4 m x 1.2 m x 0.02 m), which provide a two-dimensional (2d) waveguide environment below 5700 hz. foam wedges are applied along the sides of the test region to ensure an anechoic environment. the incident sound field is generated by an array of twenty pui audio as04008cor loud speakers, and it is measured by a g.r.a.s type 46be microphone. another g.r.a.s microphone is used to measure the transmitted/refracted sound field. the microphones are mounted onto a parker hannifin 2d traverse system which allows the entire incident and transmitted/refracted sound field to be studied. experimental aerodynamics plane wave test rig","order":68,"static_url":"/facility/8/"},{"section":"Team","title":"Hongsen Bao","url":"/people/56/","summary":"Mr. Hongsen Bao obtained his Bachelor’s Degree in Physics from Xi’an Jiaotong University in 2014, and Master’s Degree in Mechanical Engineering from University of Michigan in 2016. He joined HKUST AANTC in 2022, and his current research focuses on sound propagation and ray acous…","meta":"PhD Candidate","search_text":"hongsen bao mr. hongsen bao obtained his bachelor’s degree in physics from xi’an jiaotong university in 2014, and master’s degree in mechanical engineering from university of michigan in 2016. he joined hkust aantc in 2022, and his current research focuses on sound propagation and ray acoustics. phd candidate mr. hongsen bao obtained his bachelor’s degree in physics from xi’an jiaotong university in 2014, and master’s degree in mechanical engineering from university of michigan in 2016. he joined hkust aantc in 2022, and his current research focuses on sound propagation and ray acoustics.","order":69,"static_url":"/people/56/"},{"section":"Team","title":"Celia Bertin","url":"/people/4/","summary":"CFD, CAD modelling, Experimental testing","meta":"Research Assistant in Aerodynamics and Performance Sports Engineering","search_text":"celia bertin cfd, cad modelling, experimental testing research assistant in aerodynamics and performance sports engineering miss celia bertin obtained her bachelor degree in mechanical engineering at the hong kong university of science and technology in june 2018. for her final year project, she led a team working on the design, manufacture, and development of a robotic five-axis additive manufacturing system. in september 2019, she graduated from the university of sheffield (united kingdom) with an msc in advanced mechanical engineering with first-class honours. during her research project entitled \"computational and experimental study of flow control methods applied to fixed-wing mavs\", she conducted multiple computational fluid dynamics 3d simulations to compare the aerodynamic effects of vortex generators and boundary layer suction devices on low aspect ratio wings at low reynolds numbers. the results were validated by wind tunnel experiments. in october 2019, she joined aantc as a research assistant in aerodynamics and performance sports engineering. at aantc, she is performing high-resolution cfd simulations to study the aerodynamics of drone propellers and fuselage interaction, as well as the aerodynamics and hydrodynamics in track cycling and windsurfing, working in collaboration with the hong kong olympic teams. cfd, cad modelling, experimental testing","order":70,"static_url":"/people/4/"},{"section":"Team","title":"Haoyu Bian","url":"/people/39/","summary":"","meta":"PhD in Mechanical Engineering, HKUST","search_text":"haoyu bian phd in mechanical engineering, hkust","order":71,"static_url":"/people/39/"},{"section":"Team","title":"Huanxian Bu","url":"/people/21/","summary":"Experimental aerodynamics and aeroacoustics, aero-engine fan noise testing, drone noise testing.","meta":"Associate Professor, Northwestern Polytechnical University","search_text":"huanxian bu experimental aerodynamics and aeroacoustics, aero-engine fan noise testing, drone noise testing. associate professor, northwestern polytechnical university dr. huanxian bu joined aantc in 2016 and obtained the phd degree in hong kong university of science and technology in 2020, after he got the bachelor's and master's degrees in nanjing university of aeronautics and astronautics. his research mainly focuses on experimental aerodynamics and aeroacoustics, including aeroengine fan noise testing, uav rotor noise testing, etc. experimental aerodynamics and aeroacoustics, aero-engine fan noise testing, drone noise testing.","order":72,"static_url":"/people/21/"},{"section":"Team","title":"Xiaoyi Cai","url":"/people/66/","summary":"","meta":"PhD Student","search_text":"xiaoyi cai phd student","order":73,"static_url":"/people/66/"},{"section":"Team","title":"Sinforiano Cantos","url":"/people/16/","summary":"Aeroacoustics, CFD, rotor acoustics, optimization, sports engineering","meta":"Postdoctoral Fellow, The Hong Kong Polytechnic University","search_text":"sinforiano cantos aeroacoustics, cfd, rotor acoustics, optimization, sports engineering postdoctoral fellow, the hong kong polytechnic university sinforiano cantos obtained his bachelor’s degree in aerospace engineering from polytechnic university of valencia (spain) in 2017. for his final-year research project, he studied flutter in an airfoil using numerical simulations and experiments. he received his master’s degree in aeronautical engineering from polytechnic university of valencia in 2019. in 2018, he was an exchange student in hkust, while in 2019 he was a research trainee in the von karman institute for fluid dynamics (belgium), where he developed his final-year project. after graduation, he joined aantc as a research assistant in 2019, working on aerodynamics and sports-engineering simulations and experiments. he started his phd in september 2020. aeroacoustics, cfd, rotor acoustics, optimization, sports engineering","order":74,"static_url":"/people/16/"},{"section":"Team","title":"Cheng Cao","url":"/people/59/","summary":"","meta":"PhD Candidate","search_text":"cheng cao phd candidate","order":75,"static_url":"/people/59/"},{"section":"Team","title":"Runzhen Cao","url":"/people/61/","summary":"Runzhen Cao earned his BEng degree in Aerospace Engineering from the School of Aeronautics and Astronautics at Shanghai Jiao Tong University. In the fall of 2024, he joined AANTC as a PhD student. His research interests include noise reduction design for both aircraft systems an…","meta":"PhD Candidate","search_text":"runzhen cao runzhen cao earned his beng degree in aerospace engineering from the school of aeronautics and astronautics at shanghai jiao tong university. in the fall of 2024, he joined aantc as a phd student. his research interests include noise reduction design for both aircraft systems and subsystems, ray-tracing algorithms for low-altitude vehicle sound propagation in urban environments, and aircraft airworthiness standards within the context of low-altitude economics. phd candidate runzhen cao earned his beng degree in aerospace engineering from the school of aeronautics and astronautics at shanghai jiao tong university. in the fall of 2024, he joined aantc as a phd student. his research interests include noise reduction design for both aircraft systems and subsystems, ray-tracing algorithms for low-altitude vehicle sound propagation in urban environments, and aircraft airworthiness standards within the context of low-altitude economics.","order":76,"static_url":"/people/61/"},{"section":"Team","title":"Wangqiao Chen","url":"/people/41/","summary":"measurement acoustics; super-resolution acoustic imaging method; propeller noise;","meta":"Former Research Assistant Professor, HKUST","search_text":"wangqiao chen measurement acoustics; super-resolution acoustic imaging method; propeller noise; former research assistant professor, hkust dr. wangqiao chen received his bachelor and doctor's degree from the department of aeronautics and astronautics, at peking university (china) in 2016 and 2021. his research focuses on the understanding of aeroacoustics of fluids and engines. he has systematically examined different factors affecting the propeller trailing edge noise and proposed corresponding experimental methods which can significantly improve the interpretation of physical processes. he also investigates the super-resolution acoustic imaging method, which helps identify low-frequency sources through acoustic analogy-based tomography. in addition, the super-resolution imaging method is the first time to break through the resolution limitation of low-frequency noise source imaging and is expected to be applied to the actual industrial demand. the corresponding publication has been selected as the cover of the journal of fluid mechanics. measurement acoustics; super-resolution acoustic imaging method; propeller noise;","order":77,"static_url":"/people/41/"},{"section":"Team","title":"Haochen Chu","url":"/people/67/","summary":"","meta":"PhD Student","search_text":"haochen chu phd student","order":78,"static_url":"/people/67/"},{"section":"Team","title":"Yuzhe Dun","url":"/people/69/","summary":"","meta":"PhD Student","search_text":"yuzhe dun phd student","order":79,"static_url":"/people/69/"},{"section":"Team","title":"Yi Fang","url":"/people/5/","summary":"Experimental methods, analytical acoustics, meta-surface materials, and numerical simulations.","meta":"Former Research Fellow, AANTC","search_text":"yi fang experimental methods, analytical acoustics, meta-surface materials, and numerical simulations. former research fellow, aantc dr yi fang received her bachelor degree from nanjing university of aeronautics and astronautics (china) in 2013, major in aircraft design and engineering. in 2014, she received her msc degree from cranfield university (uk), with her major in aircraft design. she joined the advanced aircraft noise technology centre and started her phd programme at the hong kong university of science and technology in 2015. she graduated in 2018 and is now a research fellow in aantc. experimental methods, analytical acoustics, meta-surface materials, and numerical simulations.","order":80,"static_url":"/people/5/"},{"section":"Team","title":"Ryu Fattah","url":"/people/1/","summary":"Manage operations at the Aerodynamics and Acoustics Facility (formerly the Wind/Wave Tunnel Facility).","meta":"Former Wind Tunnel Engineer and Manager","search_text":"ryu fattah manage operations at the aerodynamics and acoustics facility (formerly the wind/wave tunnel facility). former wind tunnel engineer and manager dr ryu fattah is the engineer/manager of the aerodynamics and acoustics facility (aaf) at the hong kong university of science and technology (hkust). he received his meng degree in aeronautics and astronautics from the university of southampton with first-class honours in 2010. he joined the airbus noise technology centre (antc) at the university of southampton (uos) in 2010 and obtained his phd in 2016. his phd thesis focused on airframe noise, specifically by the landing gear system. he designed and conducted experiments in the uos wind tunnels, and developed the antc's high-order computational aeroacoustics code. in 2014 he became a member of a 2-year antc-airbus project that involved experiments in the airbus wind tunnel at bristol, uk. afterwards, he joined hkust in october 2016 and worked as a research fellow on high-order numerical modelling and establish the group's research into drone/uav aeroacoustics. manage operations at the aerodynamics and acoustics facility (formerly the wind/wave tunnel facility).","order":81,"static_url":"/people/1/"},{"section":"Team","title":"Jingwen Guo","url":"/people/12/","summary":"High-order numerical simulations, linearised Euler equations, duct acoustics, acoustic liners, experimental methods.","meta":"Professor, Institute of Acoustics, Chinese Academy of Sciences","search_text":"jingwen guo high-order numerical simulations, linearised euler equations, duct acoustics, acoustic liners, experimental methods. professor, institute of acoustics, chinese academy of sciences mr jingwen guo received his bachelor' degree from the department of energy power system and automation, at xi'an jiao tong university (china) in 2013. he went to tsinghua university (china) and obtained his master' degree from the department of thermal engineering in 2015. since september 2015, mr jingwen guo has been a phd student at the department of mechanical and aerospace engineering at the hong kong university of science and technology. he graduated as a phd in 2019 and is now working as a research fellow in aantc. high-order numerical simulations, linearised euler equations, duct acoustics, acoustic liners, experimental methods.","order":82,"static_url":"/people/12/"},{"section":"Team","title":"Jiahua He","url":"/people/51/","summary":"Jiahua obtained his BEng degree at Northwestern poly-technical University with a major of Aircraft design and engineering in 2020. Then he received his ME degree at the same university in 2023, major in aeroacoustics and aerodynamics. He joined the AANTC as a full-time PhD at HK…","meta":"PhD Candidate","search_text":"jiahua he jiahua obtained his beng degree at northwestern poly-technical university with a major of aircraft design and engineering in 2020. then he received his me degree at the same university in 2023, major in aeroacoustics and aerodynamics. he joined the aantc as a full-time phd at hkust in sep. 2023. phd candidate jiahua obtained his beng degree at northwestern poly-technical university with a major of aircraft design and engineering in 2020. then he received his me degree at the same university in 2023, major in aeroacoustics and aerodynamics. he joined the aantc as a full-time phd at hkust in sep. 2023.","order":83,"static_url":"/people/51/"},{"section":"Team","title":"Jiafan Hou","url":"/people/38/","summary":"Windsurfing simulation.","meta":"PhD in Mechanical Engineering, HKUST (2025)","search_text":"jiafan hou windsurfing simulation. phd in mechanical engineering, hkust (2025) jiafan hou received her b.eng degree from the chinese university of hong kong, shenzhen (cuhksz) in 2020. before joining aantc, she worked as a research assistant in robotics & artificial intelligence lab in cuhksz. she started her phd study at hkust in sep. 2021 and focused on the research of windsurfing simulation. windsurfing simulation.","order":84,"static_url":"/people/38/"},{"section":"Team","title":"Zixiang Hu","url":"/people/50/","summary":"Mr. HU Zixiang obtained his bachelor's degree and master's degree from Beihang University in 2020 and 2023 respectively. His previous major was tracked robot, especially in design, modeling, control and attitude perception. He started his PhD study at HKUST in Sept. 2023.","meta":"PhD Candidate","search_text":"zixiang hu mr. hu zixiang obtained his bachelor's degree and master's degree from beihang university in 2020 and 2023 respectively. his previous major was tracked robot, especially in design, modeling, control and attitude perception. he started his phd study at hkust in sept. 2023. phd candidate mr. hu zixiang obtained his bachelor's degree and master's degree from beihang university in 2020 and 2023 respectively. his previous major was tracked robot, especially in design, modeling, control and attitude perception. he started his phd study at hkust in sept. 2023.","order":85,"static_url":"/people/50/"},{"section":"Team","title":"Hanbo Jiang","url":"/people/6/","summary":"Computational fluid dynamics; Computational aeroacoustics Boundary element method","meta":"Assistant Professor, Eastern Institute of Technology, Ningbo","search_text":"hanbo jiang computational fluid dynamics; computational aeroacoustics boundary element method assistant professor, eastern institute of technology, ningbo dr. hanbo jiang was born in nov. 1990 in the jilin province of china. he obtained his bachelor's degree of aeronautics and astronautics at peking university (china) in 2014. he continued his study at the same university and obtained his master's degree of mechanics(dynamics and control). he was admitted to the hong kong university of science and technology in sept. 2017 and got his phd degree in jan. 2021. currently his research focuses on developing and applying numerical methods to study aeroacoustic problems, e.g., multi-propeller powered urban aerial vehicle noise. computational fluid dynamics; computational aeroacoustics boundary element method","order":86,"static_url":"/people/6/"},{"section":"Team","title":"Stanley Leung","url":"/people/47/","summary":"","meta":"Teaching Associate","search_text":"stanley leung teaching associate","order":87,"static_url":"/people/47/"},{"section":"Team","title":"Xiangru Li","url":"/people/46/","summary":"Sports Engineering Experiment; Physiology;","meta":"PhD Candidate","search_text":"xiangru li sports engineering experiment; physiology; phd candidate mr. xiangru li obtained his bachelor's degree in mechanical engineering at the university of hong kong in jun 2020. in 2020-2021, he worked as a ra at southern university of science and technology in shenzhen and developed a bio-inspired robotic fish and won the gwr of the fastest 50m swim by a robotic fish. then he received the master's degree at hkust in jun 2022, and joined the aantc as a full-time phd student in sep 2022. mr. li will focus on the sports aerodynamics coupled with physiological status. sports engineering experiment; physiology;","order":88,"static_url":"/people/46/"},{"section":"Team","title":"Xiangtian Li","url":"/people/42/","summary":"","meta":"Post-doctoral Fellow","search_text":"xiangtian li post-doctoral fellow","order":89,"static_url":"/people/42/"},{"section":"Team","title":"Yuhong Li","url":"/people/34/","summary":"Aeroelasticity and aeroacoustics, CFD and CAA","meta":"PhD in Mechanical Engineering, HKUST (2024)","search_text":"yuhong li aeroelasticity and aeroacoustics, cfd and caa phd in mechanical engineering, hkust (2024) yuhong li was born in may. 1997 in chongqing, china. he studied aeronautics and astronautics in the aerospace school at tsinghua university, and obtained his bachelor's degree in 2018. after graduation he went to imperial college london and obtained his msc in advanced computational methods for aeronautics, flow management and fluid-structure interaction with distinction. he was admitted to the hong kong university of science and technology to pursue his phd degree on sept. 2020. currently his research interest lies in theoretical and computational aeroacoustic problems of flexible wings. aeroelasticity and aeroacoustics, cfd and caa","order":90,"static_url":"/people/34/"},{"section":"Team","title":"Guangsheng Liu","url":"/people/19/","summary":"Aero-sensors; Electronic Device/Sensor Design; Vapor Liquid Microthruster; Experimental Aerodynamics","meta":"Post-doctoral Fellow","search_text":"guangsheng liu aero-sensors; electronic device/sensor design; vapor liquid microthruster; experimental aerodynamics post-doctoral fellow mr liu guangsheng obtained his bsc degree in harbor channel and coastal engineering from ocean university of china. for the final year of research, he worked on a topic about 2d numerical simulations for oscillating hydrofoil. he also has experience in control and automation system design. his project multi-rotor skid linkage rescue drone won the first prize in national marine vehicle design and production competition, 2016. he received his msc degree in aeronautical engineering from the hong kong university of science and technology, and his master research mainly focused on experimental aerodynamics and professional sports engineering. he joined in aantc as a research assistant in august 2019. aero-sensors; electronic device/sensor design; vapor liquid microthruster; experimental aerodynamics","order":91,"static_url":"/people/19/"},{"section":"Team","title":"Qian Liu","url":"/people/23/","summary":"Trailing edge noise, Elastic materials, Experimental methods","meta":"PhD in Mechanical Engineering, HKUST (2023)","search_text":"qian liu trailing edge noise, elastic materials, experimental methods phd in mechanical engineering, hkust (2023) miss liu qian obtained her bsc and msc degree in flight vehicle design from the northwestern polytechnical university in 2016 and 2019 respectively. her undergraduate dissertation is about the difference schemes of computational acoustic propagation equation. during the master period, she mainly focused on time-domain impedance boundary condition. miss liu qian joined aantc as a phd student of the joint program of the hong kong university of science and technology and southern university of science and technology in the fall of 2019. trailing edge noise, elastic materials, experimental methods","order":92,"static_url":"/people/23/"},{"section":"Team","title":"Zhida Ma","url":"/people/35/","summary":"rotor aerodynamics and aeroacoustics, the design and noise mitigation method for UAVs and eVTOL aircrafts.","meta":"Post-doctoral Fellow","search_text":"zhida ma rotor aerodynamics and aeroacoustics, the design and noise mitigation method for uavs and evtol aircrafts. post-doctoral fellow mr. ma zhida received his b.eng degree in aircraft design and engineering from nanjing university of aeronautics and astronautics (china) in 2018. his final year project was the design and implementation of a small-scale uav with distributed electric propulsion. he obtained his m.sc degree in mechanical engineering from the hong kong university of science and technology in 2020. he started his phd study at hkust in sept. 2020. rotor aerodynamics and aeroacoustics, the design and noise mitigation method for uavs and evtol aircrafts.","order":93,"static_url":"/people/35/"},{"section":"Team","title":"Jiaqi Mao","url":"/people/43/","summary":"","meta":"Post-doctoral Fellow","search_text":"jiaqi mao post-doctoral fellow","order":94,"static_url":"/people/43/"},{"section":"Team","title":"Kwan Pui Mok","url":"/people/33/","summary":"","meta":"Post-doctoral Fellow","search_text":"kwan pui mok post-doctoral fellow","order":95,"static_url":"/people/33/"},{"section":"Team","title":"Zhenjun Peng","url":"/people/49/","summary":"Zhenjun received his BEng degree from Nanjing University of Aeronautics and Astronautics with a major in Aircraft design and engineering in 2021. He received his MSc degree from Cranfield University in 2022, major in Aerospace vehicle design. He joined AANTC as a PhD student in …","meta":"PhD Candidate","search_text":"zhenjun peng zhenjun received his beng degree from nanjing university of aeronautics and astronautics with a major in aircraft design and engineering in 2021. he received his msc degree from cranfield university in 2022, major in aerospace vehicle design. he joined aantc as a phd student in the spring of 2023. phd candidate zhenjun received his beng degree from nanjing university of aeronautics and astronautics with a major in aircraft design and engineering in 2021. he received his msc degree from cranfield university in 2022, major in aerospace vehicle design. he joined aantc as a phd student in the spring of 2023.","order":96,"static_url":"/people/49/"},{"section":"Team","title":"Renhao Qu","url":"/people/36/","summary":"aeroacoustics, metasurfaces, duct acoustics","meta":"PhD in Mechanical Engineering, HKUST (2024)","search_text":"renhao qu aeroacoustics, metasurfaces, duct acoustics phd in mechanical engineering, hkust (2024) mr qu renhao obtained his bsc degree from chongqing university in 2017 and the master’s degree of mechanical engineering in shanghai jiao tong university. he joined hkust in 2020 and his current research interest is to develop the metasurfaces in aeroacoustics. aeroacoustics, metasurfaces, duct acoustics","order":97,"static_url":"/people/36/"},{"section":"Team","title":"Étienne Spieser","url":"/people/52/","summary":"I am particularly interested in the fundamental mechanisms involved in the generation of sound by flow. I am currently working on the development of analytical and numerical tools for aeroacoustics.","meta":"Researcher, Électricité de France","search_text":"étienne spieser i am particularly interested in the fundamental mechanisms involved in the generation of sound by flow. i am currently working on the development of analytical and numerical tools for aeroacoustics. researcher, électricité de france after graduating from the french aeronautical engineering school isae-supaéro, i did my doctoral studies on the modelling of sound propagation in jets at the école centrale de lyon. i am a research associate in the department of mechanical and aerospace engineering at hkust since september 2022. i am particularly interested in the fundamental mechanisms involved in the generation of sound by flow. i am currently working on the development of analytical and numerical tools for aeroacoustics.","order":98,"static_url":"/people/52/"},{"section":"Team","title":"Shivam Sundeep","url":"/people/25/","summary":"Experimental aeroacoustics, Aerodynamics flow over metamaterials, Acoustic holography.","meta":"PhD in Mechanical Engineering, HKUST (2023)","search_text":"shivam sundeep experimental aeroacoustics, aerodynamics flow over metamaterials, acoustic holography. phd in mechanical engineering, hkust (2023) i received my bachelor's degree in mechanical engineering in 2015 from sardar vallabhbhai national institute of technology (nit) india. my final year project was on solar energy storage using phase change materials. i completed my masters in thermal engineering from indian institute of technology madras (iitm) india in 2017. my research topic in masters was nearfield acoustic holography of jets and hartman whistle. after that i have worked in belcan company for two years as thermo-fluid engineer. i worked on simulation of secondary air flow and oil heat management system of rolls royce jet engines. i have joined hkust as a phd student in 2019. experimental aeroacoustics, aerodynamics flow over metamaterials, acoustic holography.","order":99,"static_url":"/people/25/"},{"section":"Team","title":"Qichen Tan","url":"/people/31/","summary":"Noise perception, UAM planning, and Human-computer interaction","meta":"Associate Professor, Soochow University","search_text":"qichen tan noise perception, uam planning, and human-computer interaction associate professor, soochow university dr. qichen tan obtained his phd degree in intelligent transportation at hkust in 2024, and obtained the beng degree in software engineering at university of electronic science and technology of china in 2020. his study focuses on noise simulation of pilotless aerial vehicle, sustainable flight path planning, and artificial intelligence. noise perception, uam planning, and human-computer interaction","order":100,"static_url":"/people/31/"},{"section":"Team","title":"Zilu Wang","url":"/people/54/","summary":"Mr. Wang Zilu received his Bachelor's degree in Engineering from Harbin Institute of Technology (China) in 2019, and then went to the Ecole Centrale de Nantes (France) to study computational mechanics and obtain his Master's degree. Mr. Wang worked as a research assistant at the…","meta":"PhD Candidate","search_text":"zilu wang mr. wang zilu received his bachelor's degree in engineering from harbin institute of technology (china) in 2019, and then went to the ecole centrale de nantes (france) to study computational mechanics and obtain his master's degree. mr. wang worked as a research assistant at the state key laboratory of aerodynamics and then at the hong kong university of science and technology. he joined aantc as a full-time doctoral student in september 2023. phd candidate mr. wang zilu received his bachelor's degree in engineering from harbin institute of technology (china) in 2019, and then went to the ecole centrale de nantes (france) to study computational mechanics and obtain his master's degree. mr. wang worked as a research assistant at the state key laboratory of aerodynamics and then at the hong kong university of science and technology. he joined aantc as a full-time doctoral student in september 2023.","order":101,"static_url":"/people/54/"},{"section":"Team","title":"Han Wu","url":"/people/8/","summary":"aeroacoustics, propeller noise, experimental method","meta":"Postdoctoral Fellow, The Hong Kong Polytechnic University","search_text":"han wu aeroacoustics, propeller noise, experimental method postdoctoral fellow, the hong kong polytechnic university mr. han wu obtained his bachelor’s degree of engineering in xi’an jiaotong university in 2017. then he went to hkust and received his msc degree. afterwards he joined aantc as a research assistant and conducted his phd study in 2020. he is currently working on the experimental investigation on the noise generated by the propellers of multi-rotor powered vehicles. aeroacoustics, propeller noise, experimental method","order":102,"static_url":"/people/8/"},{"section":"Team","title":"Yuqi Xiao","url":"/people/68/","summary":"","meta":"PhD Student","search_text":"yuqi xiao phd student","order":103,"static_url":"/people/68/"},{"section":"Team","title":"Wei Yi","url":"/people/24/","summary":"Experimental methods, computational fluid dynamics, and aeroacoustics.","meta":"Alumni","search_text":"wei yi experimental methods, computational fluid dynamics, and aeroacoustics. alumni he joined the hkust in 2018. he obtained his bachelor's degree of theoretical and applied mechanics from northwestern polytechnical university (china) in 2010. in the same year, he entered ari (aerodynamics research institute) of avic (china) and the main research area is propeller design and research, wind tunnel design and experiment. he served as the director of the wind tunnel system technology office and the director of system and aerodynamic technology office of ari. he was in charge and involved in a series of scientific research or engineering projects, including national research projects, the avic's innovation fund, national technical reform projects, etc. involving a total investment of hundreds of millions. he won the title of outstanding individual/outstanding contribution/advanced model five times in more than seven years of work, two of which are first prizes of institute -level scientific and technological achievements, and became the only one who was accelerable promoted to be an engineer in harbin branch institute in 2014. he is \"excellent youth expert in harbin\" and \"young professionals in central enterprises of china\". experimental methods, computational fluid dynamics, and aeroacoustics.","order":104,"static_url":"/people/24/"},{"section":"Team","title":"Wei Ying","url":"/people/40/","summary":"","meta":"PhD in Mechanical Engineering, HKUST (2021)","search_text":"wei ying phd in mechanical engineering, hkust (2021)","order":105,"static_url":"/people/40/"},{"section":"Team","title":"Haoyang Yu","url":"/people/65/","summary":"","meta":"PhD Student","search_text":"haoyang yu phd student","order":106,"static_url":"/people/65/"},{"section":"Team","title":"Xin Zhang","url":"/people/2/","summary":"Chair Professor","meta":"Swire Professor of Aerospace Engineering and Chair Professor","search_text":"xin zhang chair professor swire professor of aerospace engineering and chair professor prof. zhang conducts research and lectures in aerodynamics and aeroacoustics, in particular, aircraft aerodynamics and noise. he has conducted experimental and computational research in the area of unsteady aerodynamics, ground effect, aeroacoustics, and aircraft noise. he is an authority in the airframe and engine noise. he performed research in its understanding, developed novel and accurate numerical schemes for its prediction, devised methods for noise attenuation and developed predictive codes based on physics for noise prediction which are being used by industry. chair professor","order":107,"static_url":"/people/2/"},{"section":"Team","title":"Zhicheng Zhang","url":"/people/58/","summary":"","meta":"PhD Candidate","search_text":"zhicheng zhang phd candidate","order":108,"static_url":"/people/58/"},{"section":"Team","title":"Chuntai Zheng","url":"/people/22/","summary":"Experiment methods, Aerodynamics and Aeroacoustics.","meta":"Assistant Professor, Shenzhen Technology University","search_text":"chuntai zheng experiment methods, aerodynamics and aeroacoustics. assistant professor, shenzhen technology university mr. zheng chuntai has received his bachelor degree from harbin engineering university (china), school of power and energy engineering in 2014. in the same year, as a master student, he joined beihang university, school of energy and power engineering, and graduated in 2017. his master research mainly focused on turbomachinery, experimental fluid mechanics and optical measurement. in 2019, he joined the hong kong university of science and technology, the department of mechanical and aerospace engineering, as a ph.d. candidate. experiment methods, aerodynamics and aeroacoustics.","order":109,"static_url":"/people/22/"},{"section":"Team","title":"Siyang Zhong","url":"/people/3/","summary":"High-order simulations, analytical acoustics, and turbulence-aerofoil leading edge noise.","meta":"Assistant Professor, Department of Aeronautical and Aviation Engineering, The Hong Kong Polytechnic University","search_text":"siyang zhong high-order simulations, analytical acoustics, and turbulence-aerofoil leading edge noise. assistant professor, department of aeronautical and aviation engineering, the hong kong polytechnic university mr siyang zhong was born in oct. 1989 in the guizhou province of china. he obtained his bachelor's degree of theoretical and applied mechanics at peking university (china) in 2011. he continued his study at the same university and obtained his master's degree of control theory. he was admitted to the hong kong university of science and technology to pursue his phd degree on jan. 2015. he graduate as a phd in 2018. currently his research focuses on developing and applying high-order numerical methods to study aeroacoustic problems. high-order simulations, analytical acoustics, and turbulence-aerofoil leading edge noise.","order":110,"static_url":"/people/3/"},{"section":"Team","title":"Peng Zhou","url":"/people/7/","summary":"Experimental methods, MEMS and NEMS design, hydrophobic nanomaterials, and aeroacoustics.","meta":"Research Assistant Professor","search_text":"peng zhou experimental methods, mems and nems design, hydrophobic nanomaterials, and aeroacoustics. research assistant professor dr peng zhou joined aantc as a phd candidate in the fall of 2017. he received his bachelor's degree in mechanical engineering and minor in math from the hong kong university of science and technology in 2017. he has done undergraduate research about super-hydrophobic nanomaterials, and a joint research program about 2d materials at the mit eecs lab. his final year design project titled \"smart soft end effector\" won the president's cup in 2017, and was selected as one of the outstanding final year design projects. experimental methods, mems and nems design, hydrophobic nanomaterials, and aeroacoustics.","order":111,"static_url":"/people/7/"},{"section":"Team","title":"Teng Zhou","url":"/people/13/","summary":"","meta":"Lecturer in Acoustics, University of Southampton","search_text":"teng zhou lecturer in acoustics, university of southampton","order":112,"static_url":"/people/13/"},{"section":"Publications","title":"A hybrid multilevel fast multipole and equivalent source method for aeroacoustic scattering prediction","url":"/publications/161/","summary":"Lican Wang; Siyang Zhong; Bao Chen; Peng Zhou; Wangqiao Chen; Xin Zhang","meta":"Journal article · 2025","search_text":"a hybrid multilevel fast multipole and equivalent source method for aeroacoustic scattering prediction lican wang; siyang zhong; bao chen; peng zhou; wangqiao chen; xin zhang journal article · 2025 2025 10.1016/j.jsv.2025.119033","order":113,"static_url":"/publications/161/"},{"section":"Publications","title":"Acoustic imaging of geometrically shielded sound sources using tailored Green's functions","url":"/publications/160/","summary":"Lican Wang; Zhenjun Peng; Bao Chen; Zhida Ma; Wangqiao Chen; Peng Zhou; Guocheng Zhou; Siyang Zhong","meta":"Journal article · 2024","search_text":"acoustic imaging of geometrically shielded sound sources using tailored green's functions lican wang; zhenjun peng; bao chen; zhida ma; wangqiao chen; peng zhou; guocheng zhou; siyang zhong journal article · 2024 2024 10.1121/10.0034353","order":114,"static_url":"/publications/160/"},{"section":"Publications","title":"Experimental Study of the Effect of Boundary-Layer Transition on Rotor Aeroacoustics","url":"/publications/148/","summary":"Xiangtian Li; Han Wu; Yuhong Li; Peng Zhou; Siyang Zhong; Xin Zhang; Zhaokai Ma","meta":"Journal article · 2024","search_text":"experimental study of the effect of boundary-layer transition on rotor aeroacoustics xiangtian li; han wu; yuhong li; peng zhou; siyang zhong; xin zhang; zhaokai ma journal article · 2024 2024 10.2514/1.j063785","order":115,"static_url":"/publications/148/"},{"section":"Publications","title":"Enhancing sustainable urban air transportation: Low-noise UAS flight planning using noise assessment simulator","url":"/publications/147/","summary":"Qichen Tan; Yuhong Li; Han Wu; Peng Zhou; Hong Kam Lo; Siyang Zhong; Xin Zhang","meta":"Journal article · 2024","search_text":"enhancing sustainable urban air transportation: low-noise uas flight planning using noise assessment simulator qichen tan; yuhong li; han wu; peng zhou; hong kam lo; siyang zhong; xin zhang journal article · 2024 2024 10.1016/j.ast.2024.109071","order":116,"static_url":"/publications/147/"},{"section":"Publications","title":"Aerodynamics and aeroacoustics of ducted propellers: A study on the design and geometry effects","url":"/publications/146/","summary":"Sinforiano Cantos; Peng Zhou; Han Wu; Zhida Ma; Wangqiao Chen; Siyang Zhong; Xin Zhang","meta":"Journal article · 2024","search_text":"aerodynamics and aeroacoustics of ducted propellers: a study on the design and geometry effects sinforiano cantos; peng zhou; han wu; zhida ma; wangqiao chen; siyang zhong; xin zhang journal article · 2024 2024 10.1063/5.0191323","order":117,"static_url":"/publications/146/"},{"section":"Publications","title":"A numerical investigation of the aerodynamic and aeroacoustic interactions between components of a multi-rotor vehicle for urban air mobility","url":"/publications/145/","summary":"Yuhong Li; Zhida Ma; Peng Zhou; Siyang Zhong; Xin Zhang","meta":"Journal article · 2024","search_text":"a numerical investigation of the aerodynamic and aeroacoustic interactions between components of a multi-rotor vehicle for urban air mobility yuhong li; zhida ma; peng zhou; siyang zhong; xin zhang journal article · 2024 2024 10.1016/j.jsv.2023.118002","order":118,"static_url":"/publications/145/"},{"section":"Publications","title":"Sound propagation in the presence of non-isothermal sheared flow refraction and metasurface impedance reflection","url":"/publications/144/","summary":"Lican Wang; Renhao Qu; Peng Zhou; Xin Zhang","meta":"Journal article · 2024","search_text":"sound propagation in the presence of non-isothermal sheared flow refraction and metasurface impedance reflection lican wang; renhao qu; peng zhou; xin zhang journal article · 2024 2024 10.1016/j.jsv.2024.118591","order":119,"static_url":"/publications/144/"},{"section":"Publications","title":"Virtual flight simulation of delivery drone noise in the urban residential community","url":"/publications/159/","summary":"Qichen Tan; Haoyu Bian; Jingwen Guo; Peng Zhou; Hong Kam Lo; Siyang Zhong; Xin Zhang","meta":"Journal article · 2023","search_text":"virtual flight simulation of delivery drone noise in the urban residential community qichen tan; haoyu bian; jingwen guo; peng zhou; hong kam lo; siyang zhong; xin zhang journal article · 2023 2023 10.1016/j.trd.2023.103686","order":120,"static_url":"/publications/159/"},{"section":"Publications","title":"Sound reflection by periodic acoustic metasurface in sheared grazing flows","url":"/publications/158/","summary":"Renhao Qu; Jingwen Guo; Yi Fang; Wei Yi; Siyang Zhong; Xin Zhang","meta":"Journal article · 2023","search_text":"sound reflection by periodic acoustic metasurface in sheared grazing flows renhao qu; jingwen guo; yi fang; wei yi; siyang zhong; xin zhang journal article · 2023 2023 10.1016/j.ijmecsci.2022.107895","order":121,"static_url":"/publications/158/"},{"section":"Publications","title":"Predicting the aerodynamic noise of counter-rotating coaxial rotors","url":"/publications/157/","summary":"Siyang Zhong; Zhida Ma; Peng Zhou; Han Wu; Xin Zhang","meta":"Journal article · 2023","search_text":"predicting the aerodynamic noise of counter-rotating coaxial rotors 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X Zhang; C.L Morfey; P.A Nelson","meta":"Journal article · 2004","search_text":"a numerical method for computation of sound radiation from an unflanged duct x.x chen; x zhang; c.l morfey; p.a nelson journal article · 2004 2004 10.1016/j.jsv.2003.09.055","order":233,"static_url":"/publications/35/"},{"section":"Publications","title":"The evolution of co-rotating vortices in a canonical boundary layer with inclined jets","url":"/publications/34/","summary":"Xin Zhang","meta":"Journal article · 2003","search_text":"the evolution of co-rotating vortices in a canonical boundary layer with inclined jets xin zhang journal article · 2003 2003 10.1063/1.1624609","order":234,"static_url":"/publications/34/"},{"section":"Publications","title":"Off-Surface Aerodynamic Measurements of a Wing in Ground Effect","url":"/publications/33/","summary":"Xin Zhang; Jonathan Zerihan","meta":"Journal article · 2003","search_text":"off-surface aerodynamic measurements of a wing in ground effect xin zhang; jonathan zerihan journal article · 2003 2003 10.2514/2.3150","order":235,"static_url":"/publications/33/"},{"section":"Publications","title":"Influence of Diffuser Angle on a Bluff Body in Ground Effect","url":"/publications/32/","summary":"Andreas Ruhrmann; Xin Zhang","meta":"Journal article · 2003","search_text":"influence of diffuser angle on a bluff body in ground effect andreas ruhrmann; xin zhang journal article · 2003 2003 10.1115/1.1537252","order":236,"static_url":"/publications/32/"},{"section":"Publications","title":"A numerical investigation of the noise radiated by a turbulent flow over a cavity","url":"/publications/31/","summary":"G.B Ashcroft; K Takeda; X Zhang","meta":"Journal article · 2003","search_text":"a numerical investigation of the noise radiated by a turbulent flow over a cavity g.b ashcroft; k takeda; x zhang journal article · 2003 2003 10.1016/s0022-460x(02)01439-6","order":237,"static_url":"/publications/31/"},{"section":"Publications","title":"Aerodynamics of a Double-Element Wing in Ground Effect","url":"/publications/30/","summary":"Xin Zhang; Jonathan Zerihan","meta":"Journal article · 2003","search_text":"aerodynamics of a double-element wing in ground effect xin zhang; jonathan zerihan journal article · 2003 2003 10.2514/2.2057","order":238,"static_url":"/publications/30/"},{"section":"Publications","title":"Optimized prefactored compact schemes","url":"/publications/29/","summary":"Graham Ashcroft; Xin Zhang","meta":"Journal article · 2003","search_text":"optimized prefactored compact schemes graham ashcroft; xin zhang journal article · 2003 2003 10.1016/s0021-9991(03)00293-6","order":239,"static_url":"/publications/29/"},{"section":"Publications","title":"Aerodynamics of gurney flaps on a wing in ground effect","url":"/publications/28/","summary":"Jonathan Zerihan; Xin Zhang","meta":"Journal article · 2001","search_text":"aerodynamics of gurney flaps on a wing in ground effect jonathan zerihan; xin zhang journal article · 2001 2001 10.2514/3.14801","order":240,"static_url":"/publications/28/"},{"section":"Publications","title":"The Force and Pressure of a Diffuser-Equipped Bluff Body in Ground Effect","url":"/publications/27/","summary":"Andrea E Senior; Xin Zhang","meta":"Journal article · 2001","search_text":"the force and pressure of a diffuser-equipped bluff body in ground effect andrea e senior; xin zhang journal article · 2001 2001 10.1115/1.1340637","order":241,"static_url":"/publications/27/"},{"section":"Publications","title":"Some Aspects of the Aerodynamics of Gurney Flaps on a Double-Element Wing","url":"/publications/26/","summary":"David Jeffrey; Xin Zhang; David W Hurst","meta":"Journal article · 2001","search_text":"some aspects of the aerodynamics of gurney flaps on a double-element wing david jeffrey; xin zhang; david w hurst journal article · 2001 2001 10.1115/1.1334376","order":242,"static_url":"/publications/26/"},{"section":"Publications","title":"Aerodynamics of a Single Element Wing in Ground Effect","url":"/publications/25/","summary":"Jonathan Zerihan; Xin Zhang","meta":"Journal article · 2000","search_text":"aerodynamics of a single element wing in ground effect jonathan zerihan; xin zhang journal article · 2000 2000 10.2514/2.2711","order":243,"static_url":"/publications/25/"},{"section":"Publications","title":"Turbulence measurements of an inclined rectangular jet embedded in a turbulent boundary layer","url":"/publications/24/","summary":"Xin Zhang","meta":"Journal article · 2000","search_text":"turbulence measurements of an inclined rectangular jet embedded in a turbulent boundary layer xin zhang journal article · 2000 2000 10.1016/s0142-727x(00)00012-6","order":244,"static_url":"/publications/24/"},{"section":"Publications","title":"An inclined rectangular jet in a turbulent boundary layer-vortex flow","url":"/publications/23/","summary":"X Zhang","meta":"Journal article · 2000","search_text":"an inclined rectangular jet in a turbulent boundary layer-vortex flow x zhang journal article · 2000 2000 10.1007/s003480050393","order":245,"static_url":"/publications/23/"},{"section":"Publications","title":"Aerodynamics of Gurney Flaps on a Single-Element High-Lift Wing","url":"/publications/22/","summary":"David Jeffrey; Xin Zhang; David W Hurst","meta":"Journal article · 2000","search_text":"aerodynamics of gurney flaps on a single-element high-lift wing david jeffrey; xin zhang; david w hurst journal article · 2000 2000 10.2514/2.2593","order":246,"static_url":"/publications/22/"},{"section":"Publications","title":"Counter-Rotating Vortices Embedded in a Turbulent Boundary Layer with Inclined Jets","url":"/publications/21/","summary":"X Zhang","meta":"Journal article · 1999","search_text":"counter-rotating vortices embedded in a turbulent boundary layer with inclined jets x zhang journal article · 1999 1999 10.2514/2.596","order":247,"static_url":"/publications/21/"},{"section":"Publications","title":"ATTENUATION OF CAVITY FLOW OSCILLATION THROUGH LEADING EDGE FLOW CONTROL","url":"/publications/20/","summary":"X Zhang; X.X Chen; A Rona; J.A Edwards","meta":"Journal article · 1999","search_text":"attenuation of cavity flow oscillation through leading edge flow control x zhang; x.x chen; a rona; j.a edwards journal article · 1999 1999 10.1006/jsvi.1998.2012","order":248,"static_url":"/publications/20/"},{"section":"Publications","title":"Pressure over a dual-cavity cascade at supersonic speeds","url":"/publications/19/","summary":"X Zhang; J. A Edwards","meta":"Journal article · 1998","search_text":"pressure over a dual-cavity cascade at supersonic speeds x zhang; j. a edwards journal article · 1998 1998 10.1017/s000192400006509x","order":249,"static_url":"/publications/19/"},{"section":"Publications","title":"Turbulence Measurements of a Longitudinal Vortex Generated by an Inclined Jet in a Turbulent Boundary Layer","url":"/publications/18/","summary":"X Zhang","meta":"Journal article · 1998","search_text":"turbulence measurements of a longitudinal vortex generated by an inclined jet in a turbulent boundary layer x zhang journal article · 1998 1998 10.1115/1.2820736","order":250,"static_url":"/publications/18/"},{"section":"Publications","title":"The effect of trailing edge geometry on cavity flow oscillation driven by a supersonic shear layer","url":"/publications/17/","summary":"X Zhang; A Rona; J. A Edwards","meta":"Journal article · 1998","search_text":"the effect of trailing edge geometry on cavity flow oscillation driven by a supersonic shear layer x zhang; a rona; j. a edwards journal article · 1998 1998 10.1017/s0001924000065416","order":251,"static_url":"/publications/17/"},{"section":"Publications","title":"AN OBSERVATION OF PRESSURE WAVES AROUND A SHALLOW CAVITY","url":"/publications/16/","summary":"X Zhang; A Rona; J.A Edwards","meta":"Journal article · 1998","search_text":"an observation of pressure waves around a shallow cavity x zhang; a rona; j.a edwards journal article · 1998 1998 10.1006/jsvi.1998.1635","order":252,"static_url":"/publications/16/"},{"section":"Publications","title":"Nearfield Evolution of a Longitudinal Vortex Generated by an Inclined Jet in a Turbulent Boundary Layer","url":"/publications/15/","summary":"X Zhang; M. W Collins","meta":"Journal article · 1997","search_text":"nearfield evolution of a longitudinal vortex generated by an inclined jet in a turbulent boundary layer x zhang; m. w collins journal article · 1997 1997 10.1115/1.2819520","order":253,"static_url":"/publications/15/"},{"section":"Publications","title":"Measurements of a longitudinal vortex generated by a rectangular jet in a turbulent boundary layer","url":"/publications/14/","summary":"Xin Zhang; Michael W Collins","meta":"Journal article · 1997","search_text":"measurements of a longitudinal vortex generated by a rectangular jet in a turbulent boundary layer xin zhang; michael w collins journal article · 1997 1997 10.1063/1.869286","order":254,"static_url":"/publications/14/"},{"section":"Publications","title":"Progress in Computational Aeroacoustics in Predicting the Noise Radiated from Turbulent Flows","url":"/publications/13/","summary":"Geoffrey M Lilley; Xin Zhang; Aldo Rona","meta":"Journal article · 1997","search_text":"progress in computational aeroacoustics in predicting the noise radiated from turbulent flows geoffrey m lilley; xin zhang; aldo rona journal article · 1997 1997 10.20855/ijav.1997.2.106","order":255,"static_url":"/publications/13/"},{"section":"Publications","title":"Flow structure analysis around an oscillating circular cylinder at low KC number: A numerical study","url":"/publications/12/","summary":"Hui-Liu Zhang; Xin Zhang","meta":"Journal article · 1997","search_text":"flow structure analysis around an oscillating circular cylinder at low kc number: a numerical study hui-liu zhang; xin zhang journal article · 1997 1997 10.1016/s0045-7930(96)00031-x","order":256,"static_url":"/publications/12/"},{"section":"Publications","title":"Analysis of unsteady supersonic cavity flow employing an adaptive meshing algorithm","url":"/publications/11/","summary":"Xin Zhang; John A Edwards","meta":"Journal article · 1996","search_text":"analysis of unsteady supersonic cavity flow employing an adaptive meshing algorithm xin zhang; john a edwards journal article · 1996 1996 10.1016/0045-7930(95)00045-3","order":257,"static_url":"/publications/11/"},{"section":"Publications","title":"Co- and contrarotating streamwise vortices in a turbulent boundary layer","url":"/publications/10/","summary":"Xin Zhang","meta":"Journal article · 1995","search_text":"co- and contrarotating streamwise vortices in a turbulent boundary layer xin zhang journal article · 1995 1995 10.2514/3.46841","order":258,"static_url":"/publications/10/"},{"section":"Publications","title":"Compressible cavity flow oscillation due to shear layer instabilities and pressure feedback","url":"/publications/9/","summary":"Xin Zhang","meta":"Journal article · 1995","search_text":"compressible cavity flow oscillation due to shear layer instabilities and pressure feedback xin zhang journal article · 1995 1995 10.2514/3.12845","order":259,"static_url":"/publications/9/"},{"section":"Publications","title":"Experimental and numerical analysis of convective heat transfer in turbulent channel flow with square and circular columns","url":"/publications/8/","summary":"Xin Zhang; Jan Stasiek; Michael W Collins","meta":"Journal article · 1995","search_text":"experimental and numerical analysis of convective heat transfer in turbulent channel flow with square and circular columns xin zhang; jan stasiek; michael w collins journal article · 1995 1995 10.1016/0894-1777(94)00089-q","order":260,"static_url":"/publications/8/"},{"section":"Publications","title":"An experimental and computational investigation of ground effect lift loss for single jet impingement","url":"/publications/7/","summary":"Dan N Ing; Xin Zhang","meta":"Journal article · 1994","search_text":"an experimental and computational investigation of ground effect lift loss for single jet impingement dan n ing; xin zhang journal article · 1994 1994 10.1017/s0001924000049976","order":261,"static_url":"/publications/7/"},{"section":"Publications","title":"Computational analysis of a single jet impingement ground effect lift loss","url":"/publications/5/","summary":"Xin Zhang; Dan N Ing","meta":"Journal article · 1994","search_text":"computational analysis of a single jet impingement ground effect lift loss xin zhang; dan n ing journal article · 1994 1994 10.2514/3.46482","order":262,"static_url":"/publications/5/"},{"section":"Publications","title":"Flow and heat transfer in a turbulent boundary layer through skewed and pitched jets","url":"/publications/4/","summary":"Xin Zhang; Michael W Collins","meta":"Journal article · 1993","search_text":"flow and heat transfer in a turbulent boundary layer through skewed and pitched jets xin zhang; michael w collins journal article · 1993 1993 10.2514/3.11819","order":263,"static_url":"/publications/4/"},{"section":"Publications","title":"Experimental investigation of supersonic flow over two cavities in tandem","url":"/publications/3/","summary":"Xin Zhang; John A Edwards","meta":"Journal article · 1992","search_text":"experimental investigation of supersonic flow over two cavities in tandem xin zhang; john a edwards journal article · 1992 1992 10.2514/3.11049","order":264,"static_url":"/publications/3/"},{"section":"Publications","title":"An investigation of supersonic oscillatory cavity flows driven by thick shear layers","url":"/publications/2/","summary":"X Zhang; J. A Edwards","meta":"Journal article · 1990","search_text":"an investigation of supersonic oscillatory cavity flows driven by thick shear layers x zhang; j. a edwards journal article · 1990 1990 10.1017/s0001924000023319","order":265,"static_url":"/publications/2/"},{"section":"Publications","title":"Computational analysis of unsteady supersonic cavity flows driven by thick shear layers","url":"/publications/1/","summary":"X Zhang; J. A Edwards","meta":"Journal article · 1988","search_text":"computational analysis of unsteady supersonic cavity flows driven by thick shear layers x zhang; j. a edwards journal article · 1988 1988 10.1017/s0001924000016456","order":266,"static_url":"/publications/1/"},{"section":"News","title":"Prof. Zhou Peng was invited to attend the signing ceremony between bossini.X and the HK cycling team","url":"/post/36/","summary":"Prof. Zhou Peng from AANTC participated in the signing ceremony between bossini.X and the Hong Kong Cycling Team, which took place on April 18th at the Jockey Club Lecture Theatre in the Olympic Building. During the event, Professor Zhou introduced the team's newly designed next…","meta":"19 April 2024","search_text":"prof. zhou peng was invited to attend the signing ceremony between bossini.x and the hk cycling team prof. zhou peng from aantc participated in the signing ceremony between bossini.x and the hong kong cycling team, which took place on april 18th at the jockey club lecture theatre in the olympic building. during the event, professor zhou introduced the team's newly designed next-generation high-performance racing jerseys for the hong kong team. the collaboration between aantc and bossini.x leveraged the research strength of the team in aerodynamics and cycling apparel development, combined with bossini.x's expertise in sports apparel manufacturing, to comprehensively optimize the cycling jerseys. using 3d scanning technology, computational fluid dynamics simulations, and advanced wind tunnel testing, the team conducted multiple rounds of design optimization, focusing on factors such as fabric distribution and stretch ratios of the jerseys. the optimized cycling jerseys can reduce drag by up to 3% at racing speeds, giving the hong kong team a technological advantage in future competitions. 19 april 2024 sports aerodynamics","order":267,"static_url":"/post/36/"},{"section":"News","title":"The Chinese national cycling team athletes and coaches visited AANTC for communication and testing","url":"/post/35/","summary":"Recently, the athletes and coaching staff of the Chinese national cycling team visited AANTC for communication and testing purposes. AANTC, through innovative cycling apparel design, posture optimization technology, and advanced full-scale sports wind tunnel testing, along with …","meta":"19 April 2024","search_text":"the chinese national cycling team athletes and coaches visited aantc for communication and testing recently, the athletes and coaching staff of the chinese national cycling team visited aantc for communication and testing purposes. aantc, through innovative cycling apparel design, posture optimization technology, and advanced full-scale sports wind tunnel testing, along with high-precision sensors, will provide scientific recommendations for the national cycling team athletes. 19 april 2024 sports aerodynamics cyclist in the wind tunnel. prof. zhang xin and dr. li ning. aantc with the chinese national cycling team.","order":268,"static_url":"/post/35/"},{"section":"News","title":"Dr. LI Ning of Viva China Holdings Limited's visit to the Aerodynamics and Acoustics Facility","url":"/post/34/","summary":"Mr. LI Ning of Viva China Holdings Limited visited the Aerodynamics and Acoustics Facility (AAF) on the 22nd of March 2023, where some of MAE’s recent efforts using aerospace science and technologies for aero sports engineering of cycling and windsurfing are made. Prof. ZHOU Pen…","meta":"27 March 2023","search_text":"dr. li ning of viva china holdings limited's visit to the aerodynamics and acoustics facility mr. li ning of viva china holdings limited visited the aerodynamics and acoustics facility (aaf) on the 22nd of march 2023, where some of mae’s recent efforts using aerospace science and technologies for aero sports engineering of cycling and windsurfing are made. prof. zhou peng leads a team of mae students and researchers on developing aerodynamic testing, evaluating and simulation methods and tools for sports performance enhancement. the team works closely with hong kong and mainland partners. the mae team’s effort also extends to outreach activities with local high school students and teachers on stem education. 27 march 2023 sports aerodynamics","order":269,"static_url":"/post/34/"},{"section":"News","title":"HKUST and HKSI Establish Joint Center for Sports Science and Technology to Strengthen Collaboration","url":"/post/33/","summary":"The Hong Kong University of Science and Technology (HKUST) and the Hong Kong Sports Institute (HKSI) celebrated today the inauguration of the HKUST – HKSI Joint Center for Sports Science and Technology (Center). The Center will explore the integration of research and technology …","meta":"10 March 2023","search_text":"hkust and hksi establish joint center for sports science and technology to strengthen collaboration the hong kong university of science and technology (hkust) and the hong kong sports institute (hksi) celebrated today the inauguration of the hkust – hksi joint center for sports science and technology (center). the center will explore the integration of research and technology into sports, promote innovation in sports science and optimize elite athletes’ performance in international competitions. the establishment of the center was built upon a strong foundation of partnership between the parties dated back to 2018, where hkust started collaborating with the hksi to develop state-of-the-art wind tunnel testing capabilities for the development and optimization of low-drag cycling suits and gears for the hong kong cycling team, which had improved training efficiency and contributed to their performances at the tokyo 2020 olympic games. with the launch of the center, hkust’s researchers will further strengthen collaboration with hksi’s sports scientists and engineers as well as coaches on the development of new technologies, sensors, test protocols and analysis tools for sports aerodynamics, advanced training equipment and race simulations. this is aimed to optimize the sports equipment, postures and strategies of elite athletes and achieve critical marginal gains in areas including cycling, triathlon and windsurfing. over 30 representatives from hkust and hksi held the center’s first work meeting after the signing ceremony. hkust faculty presented their latest research findings in the fields of sports aerodynamics, sensors and sports performance monitoring, design and characterization of sports equipment of materials, life science engagement in sports. the two parties have also exchanged on the development, engagement of student athletes as well as internship opportunities for students. 10 march 2023 sports aerodynamics","order":270,"static_url":"/post/33/"},{"section":"News","title":"世盃比賽版足球 傳射更準有數計","url":"/post/32/","summary":"【明報專訊】今屆世界盃採用全新設計的足球Al Rihla，內藏的高靈敏度感應器為多個問題球如Ｃ朗的「上帝之髮」入球、日本翼鋒三笘薰底線助攻未有出界等，提供有力助證。雖然市面上買到的比賽版足球（$1199）未有這塊感應器，但與普通版（$259）相比，售價仍貴3倍有多，踢起來真的有什麼不同嗎？香港科技大學太古航天工程學教授兼空氣動力學和聲學實驗中心主任張欣及其團隊，將兩個足球放入低速風洞大比併，看看到底有什麼分別？ 在談足球設計之前，張欣先解釋影響足球飛行軌迹的一大因素——空氣動力學（aerodynamics），即物體在空氣中運動時所產生的各種阻力、側向力…","meta":"6 December 2022","search_text":"世盃比賽版足球 傳射更準有數計 【明報專訊】今屆世界盃採用全新設計的足球al rihla，內藏的高靈敏度感應器為多個問題球如ｃ朗的「上帝之髮」入球、日本翼鋒三笘薰底線助攻未有出界等，提供有力助證。雖然市面上買到的比賽版足球（$1199）未有這塊感應器，但與普通版（$259）相比，售價仍貴3倍有多，踢起來真的有什麼不同嗎？香港科技大學太古航天工程學教授兼空氣動力學和聲學實驗中心主任張欣及其團隊，將兩個足球放入低速風洞大比併，看看到底有什麼分別？ 在談足球設計之前，張欣先解釋影響足球飛行軌迹的一大因素——空氣動力學（aerodynamics），即物體在空氣中運動時所產生的各種阻力、側向力等。「雖然足球的射傳準確度與運動員的技術有最大關係，但當足球離腳後，影響它飛行軌迹的最重要因素便是空氣動力學。足球在空中飛行主要受兩方面影響，一個是重力，另一個是空氣流動所產生的力，皆影響足球的軌迹。」 他認為要解釋足球的空中運動，可以運用多種原理。首先是伯努利原理（bernoulli's principle），「簡單來說，它說明了當空氣的流動速度愈快，壓力便愈小。因此如果空氣流經足球左右或上下兩邊的速度不一，它的飛行軌迹便會偏向流速快的一邊，而非直線飛行」。 張欣又解釋，空氣流過足球時，並不會完全貼着足球表面，而是在一定的位置後分離，「我們通常稱為流動分離，它會在足球後方形成一個壓力很低的區域，這是足球所受空氣阻力的一個主要來源。低壓區的大小，視乎當時空氣在足球表面流動的狀態是屬於層流（laminar flow）還是湍流（turbulent flow）」。在速度比較低的時候，空氣流動較有規則，分為一層一層，之間不會互相干擾，因而稱為層流；相反速度較高，或者存在表面擾動時，空氣流動就會變成較混亂及捲動的狀態，稱為湍流。「空氣動力學中有一個重要參數『雷諾數』（reynolds number），可用於解釋當球體速度超過某一個臨界值，球表面的流動狀况會發生明顯改變，從有序的層流變成無序的湍流。相應的，流動分離點會往後移動，造成球後方的分離區域減少，阻力亦會隨之下降。」 要分析兩個版本世界盃足球在空氣動力學上的差別，張欣建議在科大空氣動力學和聲學實驗中心的低速風洞實驗室做測試，以量度在不同速度下足球的空氣動力學性能，「在風洞實驗中，我們可以在足球的表面黏貼一些纖維來觀察，氣流速度比較低的時候，可看出這些纖維擺動的方向比較一致，代表空氣流動處於層流狀態；當速度升高，纖維的擺動就變得雜亂無章，代表正受到湍流影響」。 足球周圍空氣流動狀態還可以通過煙流測試來顯示。風速較低時，空氣流動幾乎在足球的中央位置便開始分離；當風速增加，煙流在經過足球的中間點後仍會貼着球面移動，並在稍後位置才分離。先後測試過比賽版及普通版世界盃足球後，科大機械及航空航天工程學系研究助理教授周朋認為，「雖然我們看到比賽版足球的表面有很多結構，包括有較少的縫合坑紋及壓印紋理，但實際上，比賽版足球的空氣阻力與普通版在很多情况下分別不算明顯。」比賽版足球的球速不會與普通版足球有明顯差別。 不過他補充，比賽版足球的設計並非無用，實試中發現在大多數速度下，比賽版足球受到的隨機側向力都較普通版小，因此飛行路線不易改變。另一方面，在流動狀態發生改變的臨界速度區間內，比賽版足球的阻力變化都較普通版平緩。這些特點讓球員在長傳或遠射時，更準確控制傳球及射門位置。 6 december 2022 sports aerodynamics","order":271,"static_url":"/post/32/"},{"section":"News","title":"AANTC PhD student Kwan Pui Mok won the 7th HKASMSS Student Conference Award for Best Presentation","url":"/post/31/","summary":"The 7th Hong Kong Society of Sports Medicine and Science Student Academic Conference and Asian Sports Medicine Association symposium was held at Hong Kong Science and Technology Park from December 4th to 5th. Prof. Xin Zhang delivered a presentation entitled \"Advances in Aero-ba…","meta":"6 December 2021","search_text":"aantc phd student kwan pui mok won the 7th hkasmss student conference award for best presentation the 7th hong kong society of sports medicine and science student academic conference and asian sports medicine association symposium was held at hong kong science and technology park from december 4th to 5th. prof. xin zhang delivered a presentation entitled \"advances in aero-based performance sports engineering research\". as a panel member, dr. zhou peng did the bridging the gap between developers and end users: discussion on \"the obstacles and opportunities\". aantc doctoral student tom kwan pui mok presented an academic report entitled \"computational fluid dynamic simulation for track cycling strategies development\". aantc used computational fluid dynamics to discuss the aerodynamic characteristics in the process of overtaking by single vehicle, which provided a basis for the formulation of overtaking strategy by single vehicle. the presentation was awarded the 1st prize of oral presentation -- sports innovations and sports technology. congratulations, tom! 6 december 2021 sports aerodynamics","order":272,"static_url":"/post/31/"},{"section":"News","title":"AANTC’s project won the \"Tianhe Star\" Outstanding Application Award in 2021","url":"/post/30/","summary":"At the national Supercomputing Guangzhou Center 2021 Supercomputing Innovation and Application Conference held on December 3, the \"Tianhe Star\" Outstanding Application Award was selected after layers of selection. The purpose of the award is to promote the integration and innova…","meta":"6 December 2021","search_text":"aantc’s project won the \"tianhe star\" outstanding application award in 2021 at the national supercomputing guangzhou center 2021 supercomputing innovation and application conference held on december 3, the \"tianhe star\" outstanding application award was selected after layers of selection. the purpose of the award is to promote the integration and innovation of supercomputing and new technologies, and encourage users to explore and make full use of supercomputing resources to carry out research projects with scientific, economic, social and livelihood value. in 2021, the center for research in aerodynamics, acoustics and noise control technologies (aantc) won the award for its research project \"numerical simulation and drag reduction optimization design for single-vehicle aerodynamics\". over the past few years, the research team has applied advanced technologies from aviation and formula 1 racing to competitive sports using advanced computational fluid dynamics methods. special, through cooperation with olympic team, recover the real model of elite athletes, at the same time, combined with advanced sports wind tunnel test measurement, the size of wind speed, cycling posture, cycling equipment, bicycle parts, motion and so on factors to evaluate the overall size of the wind resistance and optimization, to help athletes improve performance effectively, enhance the social influence. in addition, numerical calculation also provides the flow field distribution of different body parts, which helps to optimize the design of cycling clothing. in addition, the team examined the effect of wake characteristics on aerodynamics during overtaking between competitors, providing a basis for the development of effective race measurements. for now, the research team will continue to work with professional sports teams to study the aerodynamics of high-performance sports such as cycling and windsurfing (windsurfing). the results of the research will help coaches and athletes improve their training as well as carry out basic scientific research. 6 december 2021 sports aerodynamics cfd simulation.","order":273,"static_url":"/post/30/"},{"section":"News","title":"Bluff body research reveals the mechanics of surface pattern on drag reduction and sound attenuation","url":"/post/29/","summary":"In cycling sports, the aerodynamic skinsuit plays a significant role as reductions of the aerodynamic drag would improve athlete's performance. Recently, the research team explored the design principles of the aerodynamic skinsuit. By conducting cylinder wind tunnel tests within…","meta":"15 November 2021","search_text":"bluff body research reveals the mechanics of surface pattern on drag reduction and sound attenuation in cycling sports, the aerodynamic skinsuit plays a significant role as reductions of the aerodynamic drag would improve athlete's performance. recently, the research team explored the design principles of the aerodynamic skinsuit. by conducting cylinder wind tunnel tests within the range of cycling speed based reynolds numbers, the research team found the sports fabric with longitudinal grooves can achieve a drag reduction over 50% and a maximum noise attenuation over 15db. the research team also linked such variations to the near-field flow measurements in different flow regimes, revealing the fluid mechanics behind them. this research enables the design of the best aerodynamic skinsuit, helping athletes to improve their performance. the work is published in the reputed fluid dynamics journal physics of fluids. https://doi.org/10.1063/5.0070959 15 november 2021 sports aerodynamics","order":274,"static_url":"/post/29/"},{"section":"News","title":"Windsurfing analysis breaks down propulsion mechanics of sailboards","url":"/post/28/","summary":"Windsurfers often pump their sails back and forth to gain speed, but it can also cause slowing if done incorrectly. The complicated physics of the action was tackled by our group. Recently, the research group examined the propulsive dynamics of sail pumping on sailboards and est…","meta":"12 October 2021","search_text":"windsurfing analysis breaks down propulsion mechanics of sailboards windsurfers often pump their sails back and forth to gain speed, but it can also cause slowing if done incorrectly. the complicated physics of the action was tackled by our group. recently, the research group examined the propulsive dynamics of sail pumping on sailboards and established two quantities that measure the propulsive performance of pumping sails. the work is published on the reputed fluid dynamics journal physics of fluids, and was selected as featured on cover. the aip scilight reported the progress https://aip.scitation.org/doi/10.1063/10.0006710. 12 october 2021 sports aerodynamics windsurfing simulation by aantc.","order":275,"static_url":"/post/28/"},{"section":"News","title":"行政长官祝贺李慧诗勇夺东京奥运铜牌","url":"/post/27/","summary":"AANTC团队为香港单车队精英选手李慧诗进行多轮风洞试验，对骑行姿态、器材、服装进行空气动力学优化，助力李慧诗在二○二○年东京奥运会女子场地单车争先赛中夺得铜牌，行政长官林郑月娥致以热烈祝贺。林郑月娥说：「李慧诗是首名分别于两届奥运会夺得奖牌的香港运动员，她的实力和决心经得起时间考验，成绩斐然，创造香港体坛传奇，全港市民都对她取得的成就感到欣喜。近年香港单车馆为香港单车运动员提供顶级的比赛和训练场地，单车队亦积极和本地大学合作，运用科研成果提升运动员表现。李慧诗和单车队的成功，为体育发展的方向和提升精英运动员培训带来启示，我们一定会更重视这些方面的资源…","meta":"8 August 2021","search_text":"行政长官祝贺李慧诗勇夺东京奥运铜牌 aantc团队为香港单车队精英选手李慧诗进行多轮风洞试验，对骑行姿态、器材、服装进行空气动力学优化，助力李慧诗在二○二○年东京奥运会女子场地单车争先赛中夺得铜牌，行政长官林郑月娥致以热烈祝贺。林郑月娥说：「李慧诗是首名分别于两届奥运会夺得奖牌的香港运动员，她的实力和决心经得起时间考验，成绩斐然，创造香港体坛传奇，全港市民都对她取得的成就感到欣喜。近年香港单车馆为香港单车运动员提供顶级的比赛和训练场地，单车队亦积极和本地大学合作，运用科研成果提升运动员表现。李慧诗和单车队的成功，为体育发展的方向和提升精英运动员培训带来启示，我们一定会更重视这些方面的资源配合。」李慧诗是香港首位女子单车比赛世界冠军，她自二○○四年成为全职运动员，多次出赛为香港扬威国际体坛，包括于二○一○年、二○一四年及二○一八年亚洲运动会在多项赛事取得金牌，以及分别在二○一三年及二○一九年在世界锦标赛夺冠。 8 august 2021 sports aerodynamics 香港单车运动员李慧诗在二○二○年东京奥运会女子场地单车争先赛中为香港夺得铜牌！ 李慧詩在aantc风洞实验室进行训练。 李慧詩在aantc风洞实验室进行训练。","order":276,"static_url":"/post/27/"},{"section":"News","title":"CE congratulates Lee Wai-sze on winning bronze medal at Tokyo Olympics","url":"/post/26/","summary":"AANTC team conducted a multi-round wind tunnel test for Hong Kong cycling athlete Lee Wai-sze, to optimize the riding posture, equipment, and clothing to help her win the bronze medal in the women's track cycling race at the Tokyo Olympic Games in 2020. The Chief Executive, Mrs …","meta":"8 August 2021","search_text":"ce congratulates lee wai-sze on winning bronze medal at tokyo olympics aantc team conducted a multi-round wind tunnel test for hong kong cycling athlete lee wai-sze, to optimize the riding posture, equipment, and clothing to help her win the bronze medal in the women's track cycling race at the tokyo olympic games in 2020. the chief executive, mrs carrie lam, extended her greatest congratulations to her. \"lee wai-sze is the first hong kong athlete who has won medals at two olympic games. she has demonstrated that her competence and determination have passed the test of time, and she has become a hong kong legend with her brilliant results. all hong kong people are overjoyed at her achievements. \"the hong kong velodrome has provided hong kong cycling athletes with a top-notch competition and training venue in recent years. the cycling team has also collaborated with a local university to leverage scientific research achievements to enhance the performance of athletes. the success of lee wai-sze and the cycling team has provided insights into the direction of sports development and training of elite athletes. we will attach more importance to the allocation of resources in these areas,\" mrs lam said. lee wai-sze is the first hong kong world champion in women's cycling competitions. as a full-time athlete since 2004, she has brought hong kong honour in the international sporting arena with outstanding results, including gold medals in various competitions of the asian games in 2010, 2014 and 2018 as well as gold medals at the world championships in 2013 and 2019. 8 august 2021 sports aerodynamics lee wai-sze won a bronze medal in the women's sprint even in the tokyo 2020 olympic games for hk lee wai-sze is training in aantc wind tunnel lee wai-sze is training in aantc wind tunnel","order":277,"static_url":"/post/26/"},{"section":"News","title":"Sarah Lee's wind tunnel test before Tokyo Olympics","url":"/post/25/","summary":"Our Performance Sports Engineering team has been collaborating with Hong Kong Sports Institute to improve the aerodynamic performance of their elite cyclists. Recently, we have done wind tunnel tests for Sarah Lee, one of the top track cyclists in Hong Kong, to prepare for Tokyo…","meta":"27 April 2021","search_text":"sarah lee's wind tunnel test before tokyo olympics our performance sports engineering team has been collaborating with hong kong sports institute to improve the aerodynamic performance of their elite cyclists. recently, we have done wind tunnel tests for sarah lee, one of the top track cyclists in hong kong, to prepare for tokyo olympics. the research activities are greatly supported by mr. adam kwok, executive director of shkp, through his generous donation. 27 april 2021 sports aerodynamics","order":278,"static_url":"/post/25/"},{"section":"News","title":"Ray-tracing of drone noise","url":"/post/20/","summary":"The in-house ENVironmental Acoustic Ray-tracing Code (EnvARC) at the AANTC generates acoustic maps using generalized acoustic sources, generic terrain and building models with user-defined impedances, and resolves the effects of atmospheric sound absorption and refraction. The i…","meta":"25 February 2020","search_text":"ray-tracing of drone noise the in-house environmental acoustic ray-tracing code (envarc) at the aantc generates acoustic maps using generalized acoustic sources, generic terrain and building models with user-defined impedances, and resolves the effects of atmospheric sound absorption and refraction. the inputs consist of the noise source and environmental scenario models as well as the observer positions. the output is the noise exposure map for noise evaluation and abatement. 25 february 2020 drone projects","order":279,"static_url":"/post/20/"},{"section":"News","title":"Variation of the spanwise vorticity on a pitching airfoil","url":"/post/19/","summary":"The instantaneous flow pattern on a pitching airfoil is acquired by a high-speed PIV system, which can achieve the highest sampling rate of 1633Hz. This figure gives the development of the vorticity near the trailing edge during the half pitching cycle.","meta":"25 February 2020","search_text":"variation of the spanwise vorticity on a pitching airfoil the instantaneous flow pattern on a pitching airfoil is acquired by a high-speed piv system, which can achieve the highest sampling rate of 1633hz. this figure gives the development of the vorticity near the trailing edge during the half pitching cycle. 25 february 2020 aeroacoustics","order":280,"static_url":"/post/19/"},{"section":"News","title":"Garment design using advanced CFD techniques","url":"/post/18/","summary":"The studies on the garment are being conducted in the PSE group to provide the most efficient drag reduction design for athletes based on cutting-edge CFD simulations. The flow field varies among different riders due to various figures and body postures. High-resolution CFD simu…","meta":"25 February 2020","search_text":"garment design using advanced cfd techniques the studies on the garment are being conducted in the pse group to provide the most efficient drag reduction design for athletes based on cutting-edge cfd simulations. the flow field varies among different riders due to various figures and body postures. high-resolution cfd simulations can help visualize the wall shear stress from which we can locate the exact position where separation or reattachment occurs. for each flow region, the ad-hoc design can then be applied accordingly. 25 february 2020 sports aerodynamics","order":281,"static_url":"/post/18/"},{"section":"News","title":"Students of AANTC attending AIAA conference in Delft","url":"/post/17/","summary":"PhD students of AANTC attended and presented at 25th AIAA/CEAS Aeroacoustics Conference in Delft, Netherlands. Students presented their own works and shared their research results with scholars all over the world.","meta":"25 February 2020","search_text":"students of aantc attending aiaa conference in delft phd students of aantc attended and presented at 25th aiaa/ceas aeroacoustics conference in delft, netherlands. students presented their own works and shared their research results with scholars all over the world. 25 february 2020 general","order":282,"static_url":"/post/17/"},{"section":"News","title":"Collaboration with HKSI on bicycle aerodynamic research","url":"/post/16/","summary":"PSE team is collaborating with HKSI to help enhance elite cyclists' performance aiming at the Tokyo 2020 Olympics. The collaboration received a donation from Mr Adam KWOK, Executive Director of SHKP. Head cycling coach Mr SHEN Jinkang and the world champion LEE Wai-sze are also …","meta":"25 February 2020","search_text":"collaboration with hksi on bicycle aerodynamic research pse team is collaborating with hksi to help enhance elite cyclists' performance aiming at the tokyo 2020 olympics. the collaboration received a donation from mr adam kwok, executive director of shkp. head cycling coach mr shen jinkang and the world champion lee wai-sze are also highly involved in the program and will provide professional advice on performance improvement. 25 february 2020 sports aerodynamics","order":283,"static_url":"/post/16/"},{"section":"News","title":"Chairman and president of AVIC visited AANTC","url":"/post/15/","summary":"The chairman and president of AVIC visited AANTC in the company of Prof. Xin Zhang and Prof. Wei Shyy. Students from AANTC gave demonstrations of their latest research works, and the academic output from the centre was highly spoken of. The cooperation between AVIC and HKUST sta…","meta":"25 February 2020","search_text":"chairman and president of avic visited aantc the chairman and president of avic visited aantc in the company of prof. xin zhang and prof. wei shyy. students from aantc gave demonstrations of their latest research works, and the academic output from the centre was highly spoken of. the cooperation between avic and hkust starts from 2012 and remarkable success has been achieved especially in aerodynamic and acoustic researches. 25 february 2020 general","order":284,"static_url":"/post/15/"},{"section":"News","title":"Swire Trust visits School of Aeronautical Engineering","url":"/post/14/","summary":"Swire Trust Group visited the School of Aeronautical Engineering with Prof. Zhang for the latest advancement in noise prediction and reduction research from AANTC (01/2018).","meta":"25 February 2020","search_text":"swire trust visits school of aeronautical engineering swire trust group visited the school of aeronautical engineering with prof. zhang for the latest advancement in noise prediction and reduction research from aantc (01/2018). 25 february 2020 general","order":285,"static_url":"/post/14/"},{"section":"News","title":"HKUST Executive Vice-President and Provost visits AANTC","url":"/post/13/","summary":"Professor Wei Shyy, the Executive Vice-President and Provost of HKUST visited the AANTC laboratory accompanied by Prof Xin Zhang and Prof Xun Huang (11/2017). Professor Shyy visited the acoustic and aeroacoustic laboratories. AANTC PhD students briefed Prof. Shyy about their res…","meta":"25 February 2020","search_text":"hkust executive vice-president and provost visits aantc professor wei shyy, the executive vice-president and provost of hkust visited the aantc laboratory accompanied by prof xin zhang and prof xun huang (11/2017). professor shyy visited the acoustic and aeroacoustic laboratories. aantc phd students briefed prof. shyy about their research. 25 february 2020 general","order":286,"static_url":"/post/13/"},{"section":"Opportunities","title":"(New!) PhDs and Research Fellowships in Aerodynamics and Aeroacoustics","url":"/career/30/","summary":"- Experimental aerodynamics and aeroacoustics - Computational aeroacoustics and aerodynamics - Rotor/helicopter aerodynamics and aeroacoustics - Low-noise urban air mobility development - Aircraft noise, including airframe and engine noise - Advanced aerodynamic design of sports…","meta":"Recruitment status not verified","search_text":"(new!) phds and research fellowships in aerodynamics and aeroacoustics - experimental aerodynamics and aeroacoustics - computational aeroacoustics and aerodynamics - rotor/helicopter aerodynamics and aeroacoustics - low-noise urban air mobility development - aircraft noise, including airframe and engine noise - advanced aerodynamic design of sports equipment - low-altitude aircraft noise assessment and prediction - sports-engineering aerodynamics - physics-informed machine learning - urban air mobility vehicle control and route planning recruitment status not verified candidates with background in aerodynamics, aeroacoustic engineering, mechanical engineering, applied mathematics, etc., are welcome. if you are interested, please send your cv to professor peng zhou (pengzhou@ust.hk). phd students: sept. 2026 and feb. 2026; research fellows: all year round. phd students: sept. 2026 and feb. 2026; research fellows: oct 2025 and after. student","order":287,"static_url":"/career/30/"},{"section":"Opportunities","title":"Research Assistant (RA) in Aerodynamics, Aeroacoustics, and Aircraft Design","url":"/career/32/","summary":"Several Research Assistant (RA) positions are available at the Aerodynamics Acoustics and Noise control Technology Centre (AANTC), HKUST. These roles offer a unique opportunity to advance aerospace engineering through innovative projects in aerodynamics, aeroacoustics, aircraft …","meta":"Recruitment status not verified","search_text":"research assistant (ra) in aerodynamics, aeroacoustics, and aircraft design several research assistant (ra) positions are available at the aerodynamics acoustics and noise control technology centre (aantc), hkust. these roles offer a unique opportunity to advance aerospace engineering through innovative projects in aerodynamics, aeroacoustics, aircraft structural design, and flight control systems. successful candidates will contribute to multi-year research initiatives, working with state-of-the-art facilities, including wind tunnels, 3d printing labs, and flight simulators. the research focuses on developing noise mapping software, optimizing 3d-printed aircraft structures, and enhancing flight control systems for precision navigation. opportunities for phd/mphil studies may be available. key responsibilities can be in one or more fields below: ✅ aircraft structural design and 3d printing manufacturing ✅ flight control system design and optimization ✅ noise mapping and visualization software development recruitment status not verified requirements key requirements include (but are not necessarily mandatory): • bachelor’s or master's degree in aerospace engineering, mechanical engineering, computer science, electrical engineering, or related fields. • proficiency in cad software (e.g., solidworks, catia), fea tools (e.g., ansys), or programming languages (e.g., python, c++, matlab). • experience in aeroacoustics, cfd, 3d printing, or flight control systems is an advantage. • familiarity with embedded systems, sensor integration, or computer graphics (e.g., opengl, vtk) is desirable. • strong skills in data analysis, experimental techniques, or software development. • experience in engineering competitions (e.g., sae aero design, uav challenges) is highly desirable. • technical report writing in english. • fluency in english (required) and mandarin (desirable). june 1, 2025 and onwards. if you are interested, please send your cv to professor peng zhou (pengzhou@ust.hk). june 1, 2025 and onwards. research assistant","order":288,"static_url":"/career/32/"},{"section":"Opportunities","title":"Research Assistant (RA) and Research Fellow (RF) in Sports-Engineering Aerodynamics","url":"/career/29/","summary":"Key responsibilities can be in one or more fields below: - Mechanical design, assembly and commissioning of advanced sports aerodynamic test rigs and high-quality fan arrays. - Develop an active turbulence generator for wind tunnel testing. - Use 3D scan to reconstruct 3D geomet…","meta":"Recruitment status not verified","search_text":"research assistant (ra) and research fellow (rf) in sports-engineering aerodynamics key responsibilities can be in one or more fields below: - mechanical design, assembly and commissioning of advanced sports aerodynamic test rigs and high-quality fan arrays. - develop an active turbulence generator for wind tunnel testing. - use 3d scan to reconstruct 3d geometry of athletes and equipment for aerodynamic analysis. - use computational fluid dynamics to analyze the key flow features around athletes and equipment. - develop automatic flow measurement capability in wind tunnels based on a robotic arm. - circuit design and debugging for sensor systems used for sports field tests. - develop mobile apps and bike computer applications for sports sensor data collection and display. - develop computer vision codes to analyze the athlete's posture and equipment deformation during wind tunnel tests and field tests. recruitment status not verified key requirements include (but are not necessarily mandatory): - bachelor (ra) and phd (rf) in mechanical, aerospace engineering, electronic and computer engineering or automation. - familiar with cad or eda software. - experience in experimental techniques, data processing and uncertainty analysis will be an advantage. - experience in electronics and/or robotics system design will be an advantage. - technical report writing in english. - fluency in english (required) and mandarin (desirable). job start date: 1st april 2023 and onwards. salary: 18,000–21,000 hkd/month (ra) and 22,000 – 32,000 hkd/month (rf); negotiable. if you are interested, please send your cv to professor peng zhou (pengzhou@ust.hk). 1st april 2023 and onwards research assistant","order":289,"static_url":"/career/29/"}]
