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《AERONAUTICAL COMPUTER TECHNIQUE》 1998-01
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Numerical Simulations of 3-D Supersonic Inlet Flowfields

Feng Jianhu(Department of Applied Mathematics, Northwestern Polytechnical University, Xi'an 710072)  
In this paper,three-dimensional Supersonic inlet flowfields have been calculated.The governing equations are nonsteady compressible Navier-Stokes equations. The discretization was Jameson's Runge-Kutta finite volume method. Modified Baldwin-Lomax algebraic eddyviscosity turbulent model and the wall function law were used. A new viscous terms discretization in the frame of finite volume method was adopted. For convergence acceleration,local time stepping,implicit residual average and artificial dissipation techniques were also used.A aircraft inlet flowfields of several flight states were calculated. The mean total pressure recovery and total pressure distortion across the engine face were obtained. These results were compared with experiment data and were proved to be satisfactory.
【CateGory Index】: V231.3
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【Co-citations】
Chinese Journal Full-text Database 1 Hits
1 Feng Jianhu (Dept. of Applied Mathematics,Northwestern Polytechnical University,Xi′an 710072);NAVIER-STOKES PREDICTIONS OF 2-D VECTORED NOZZLE FLOWS[J];Journal of Aerospace Power;1996-03
【Co-references】
Chinese Journal Full-text Database 10 Hits
1 Zhu Yu , Li Chunxuan , Li Tian(1. Shenyang Aircraft Design & Research Institute, Shenyang 110035, China)(2. National Laloratory for Computational Fluid Dynamics, Beijng University of Aeronautics and Astronautics, Beijmg 100083, China);EFFECT OF AIRFRAME ON SUPERSONIC INLET PERFORMENCE[J];Aircraft Design;2001-02
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