24 results on '"Bai, Junqiang"'
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2. Fast flow field prediction approach of supersonic inlet in wide operating range based on deep learning
3. Aerodynamic shape optimization of the vortex-shock integrated waverider over a wide speed range
4. Improved hybrid model for transitional separated flows over a rough compressor blade
5. Numerical investigation of the unstart flow at off-design condition of REST inlet at a Mach of 4
6. Numerical study of the hysteresis effect on the supercritical airfoil for the transonic circulation control
7. Multi-objective aerodynamic optimization of two-dimensional hypersonic forebody-inlet based on the heuristic algorithm
8. Deep learning based multistage method for inverse design of supercritical airfoil
9. An efficient adjoint method for the aero-stealth shape optimization design
10. Three-dimensional pore-scale study of the directional heat transfer in a high thermal conductivity carbon/carbon composite protection system
11. Numerical study of the suction flow control of the supersonic boundary layer transition in a framework of gas-kinetic scheme
12. Hybrid computational aeroacoustics approach based on the synthetic turbulence model in Eulerian description
13. Fast pressure distribution prediction of airfoils using deep learning
14. An effective low dissipation method for compressible flows
15. An inverse design method with aerodynamic design optimization for wing glove with hybrid laminar flow control
16. Aerodynamic optimization of civil aircraft with wing-mounted engine jet based on adjoint method
17. A gradient-based aero-stealth optimization design method for flying wing aircraft
18. Research of transition criterion for semi-empirical prediction method at specified transonic regime
19. Numerical investigation of the supersonic stabilizing parachute's heating loads
20. A grid strategy for predicting the space plane's hypersonic aerodynamic heating loads
21. Development of a computational fluid dynamics compatible mathematical model for boundary layer transitional flows in low-disturbance environment
22. Capturing transition with flow–structure–adaptive KDO RANS model
23. Study of boundary layer transition on supercritical natural laminar flow wing at high Reynolds number through wind tunnel experiment
24. WITHDRAWN: A robust and high-fidelity aerodynamic optimization design of truss-braced-wing aircraft with gradient-based method
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