A5073274195- Computational Fluid Dynamics and Aerodynamics
- Fluid Dynamics and Turbulent Flows
- Gas Dynamics and Kinetic Theory
- Plasma and Flow Control in Aerodynamics
- Aerodynamics and Acoustics in Jet Flows
- Aerodynamics and Fluid Dynamics Research
- Wind and Air Flow Studies
- Model Reduction and Neural Networks
- Particle Dynamics in Fluid Flows
- Advanced Sensor and Energy Harvesting Materials
- Probabilistic and Robust Engineering Design
- Metal and Thin Film Mechanics
- Rocket and propulsion systems research
- Aerospace and Aviation Technology
- Semiconductor materials and devices
- ZnO doping and properties
- Nuclear Engineering Thermal-Hydraulics
- Advanced Numerical Methods in Computational Mathematics
- Turbomachinery Performance and Optimization
- Geotechnical and Geomechanical Engineering
- Generative Adversarial Networks and Image Synthesis
- Shape Memory Alloy Transformations
- Electromagnetic Compatibility and Measurements
- Laser and Thermal Forming Techniques
- Interactive and Immersive Displays
Northwestern Polytechnical University
2019-2024
ShanghaiTech University
2024
Xi'an Aeronautical University
2020-2022
University of Hong Kong
2020-2022
Hong Kong University of Science and Technology
2020-2022
Beihang University
2017-2020
Kowloon Hospital
2020
Shanghai Jiao Tong University
2017
Wuhan University
2016
Xi'an Technological University
2013
A novel multidimensional strain sensor mimicking human skin is developed. In-plane and pressure subsensors are integrated into a with exceptional sensitivity selectivity capable of detecting stimuli from 3D directions.
Reducing the design variable space is crucial in multi-objective airfoil profile optimization to improve efficiency and reduce computational costs. Based on random forest deep neural networks (DNNs), this work performs range reduction ten variables obtained through a fourth-order class shape transformation parameterization method for subsonic profiles. Three aerodynamic performance objectives (lift coefficient, drag lift-to-drag ratio) are evaluated using Reynolds-averaged Navier–Stokes...
Localized acoustic receptivity experiments are conducted on a two-dimensional flat plate in low-turbulence wind tunnel. Discrete wavelet transform (DWT) is employed to detect and identify Stokes waves Tollmien–Schlichting (T-S) within the boundary layer. The effects of disturbance frequency roughness thickness amplitude T-S examined separately low-speed regime. phase velocities at each measurement location validated found be good agreement with theoretical predictions. Additionally, velocity...
The precise identification of aerodynamic parameters for aircraft is increasingly critical in design endeavors, particularly furnishing accurate dynamic models ground and flight simulation. To mitigate the dependence on traditional methods that rely heavily models, this work introduces an methodology based Physics-informed Neural Networks (PINNs). By utilizing six degrees freedom motion equation as physical constraint with neural network, to be identified network variables, model trained...
The Reynolds Averaged Navier-Stokes (RANS) models are still the workhorse in current engineering applications due to its high efficiency and robustness. However, closure coefficients of RANS turbulence determined by model builders according some simple fundamental flows, suggested values may not be applicable complex especially supersonic jet interaction flow. In this work, Bayesian method is employed recalibrate Spalart-Allmaras (SA) improve performance problem quantify uncertainty wall...
Two kinds of BFRs in three WEEE plastics(cell phone shells, computer housings and TV housings) PCBs were detected with GC/MS. The results showed the plastics used as mobile shells had no BFRs. TBBPA was only found housings. Among PBDEs, congeners heptabromodiphenyl ether, octabromodiphenyl ether nonabromodiphenyl frequent ones, both But contents N9BDE lower than other two, 180 mg/kg 5.3 respectively, while pentabromodiphenyl hexabromodiphenyl determined PCBs.
Morphing aircraft is an important trend in the future development of next-generation aircraft. This paper focuses on with a small aspect ratio flying wing configuration that includes morphing tails. The unsteady aerodynamic characteristics tail are numerically simulated using unstructured overset grid technique and dual-time method, focusing effects deflection angle over time, Mach number, side slip entire second derivative time should be continuous, maximum angular velocity acceleration...
In this study, we propose a scheme to control the deflection of warhead based on configuration hypersonic glide body (HGB) solve problems posed by its large surface load and severe aerodynamic heat under flight conditions. We conducted numerical simulations configurations an HGB analog different modes as well varying angles directions deflection. The results showed that once had been deflected, overall still exhibited static longitudinal stability. An increase in angle significantly reduced...
Aerodynamic/stealth design is becoming an important factor in the advanced airfoil design. In this work, a supervised machine learning method proposed for aerodynamic and stealth integrated The conditional generative adversarial network (CGAN) constructed multidisciplinary of airfoil. Then, generator discriminator simply using deep neural have good robustness stability training. CGAN model also shows generalization capability test set, with less than 1% error fitting to profile data,...
This paper investigates the effects of local porous uniform blowing on skin-friction drag reduction in spatially developing compressible turbulent boundary layers through direct numerical simulations. Under influence blowing, decreases drastically within controlled regions, and effect extends downstream. The rate exceeds 10% for velocities considered herein. intrinsic mechanism decreased is further explored, terms various contributions to this quantity, Reynolds shear stress budget,...
This paper develops a low-diffusion robust flux splitting scheme termed TVAP to achieve the simulation of wide-ranging Mach number flows. Based on Toro-Vázquez approach, new splits inviscid into convective system and pressure system. method introduces function numerical sound speed evaluate advection Meanwhile, diffusion term, momentum flux, interface velocity are constructed measure Then, typical test problems utilized systematically assess robustness accuracy resulting scheme. Matrix...