Volume 29 Issue 8
Aug.  2014
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SHI Lei, YAN Ming, YANG Yun-jun, ZHOU Wei-jiang. Applicability investigation about several common schemes and turbulence models in high speed flow[J]. Journal of Aerospace Power, 2014, (8): 1904-1910. doi: 10.13224/j.cnki.jasp.2014.08.019
Citation: SHI Lei, YAN Ming, YANG Yun-jun, ZHOU Wei-jiang. Applicability investigation about several common schemes and turbulence models in high speed flow[J]. Journal of Aerospace Power, 2014, (8): 1904-1910. doi: 10.13224/j.cnki.jasp.2014.08.019

Applicability investigation about several common schemes and turbulence models in high speed flow

doi: 10.13224/j.cnki.jasp.2014.08.019
  • Received Date: 2013-08-31
  • Publish Date: 2014-08-28
  • Several common spatial dispersion schemes and turbulence models in current computational fluid dynamics were compared and analyzed to investigate complex flow phenomenons such as strong shock waves, shock waves/boundary layer interaction, flow separation and turbulent flow in hypersonic flight. The results demonstrate that the resolutions of strong shock waves are the same by different schemes. Roe and LDE (low diffusion E-CUSP (convective upwind split pressure)) schemes show better agreement in friction coefficient and heat transfer coefficient with experimental data than other schemes. The friction coefficient predicted by S-A (Spalart-Allmaras) turbulence model is greater than that by k-ω SST (shear stress transport) turbulence model about 10%. The separation zone of the latter is twice the size of the former and the separation point is located in front.

     

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  • [1]
    Armstrong J G.Flight planning and conduct of the X-15A-2 envelope expansion program[R].[S.l.]:Air Force Flight Test Center,AFFTC-TD-69-4,1969.
    [2]
    Rasky D J,Pittman R B,Newfield M E.The reusable launch vehicle challenge[R].AIAA-2006-7208,2006.
    [3]
    Leonard C P,Amundsen R M,Bruce W E.Hyper-X hot structures design and comparison with flight data[R].AIAA-2005-3438,2005.
    [4]
    Levy D W,Vassberg J.Summary of data from the first AIAA CFD drag prediction workshop[R].AIAA-2002-0841,2002.
    [5]
    Vassberg J C.Drag prediction for the DLR-F4 wing/body using OVERFLOW and CFL3D on the overset mesh[R].AIAA-2002-0840,2002.
    [6]
    Alliance N.CFD verification and validation web site[EB/OL].[2011-01-01].http://www.grc.nacs.gov/www/wind/valid.htm.
    [7]
    Steger J L,Warming R F.Flux vector splitting of the inviscid gas-dynamic equations with application to finite-difference method[J].Journal of Computational Physics,1981,40(2):263-293.
    [8]
    Roe P L.Approximate riemann solvers,parameter vector and difference scheme[J].Journal of Computational Physics,1981,43(2):357-372.
    [9]
    Hanel D.On the accuracy of upwind scheme in the solution of Navier-Stokes equation[R].AIAA 87-1105,1987.
    [10]
    Liou M S.A sequel to AUSM:AUSM+[J].Journal of Computational Physics,1996,129(2):364-382.
    [11]
    Chima R V,Liou M S.Comparison of the AUSM+ and H-CUSP schemes for turbomachinery applications[R].AIAA-2003-4120,2003.
    [12]
    WANG Baoyuan,ZHA Gecheng.Comparison of a low diffusion E-CUSP and the Roe scheme for RANS calculation[R].AIAA-2008-0569,2008.
    [13]
    Lyubimov A N,Rusanov V V.Gas flows past blunt bodies .NASA TT F-715,1970.
    [14]
    Chaupt E,Dubois F.FLU3PNS:a three-dimensional thin layer and parabolized Navier-Strokes solver using the MUSCL upwind scheme[R].AIAA 91-0728,1991.
    [15]
    Coles D.Measurements in the boundary layer on a smooth flat plate in supersonic flow:Ⅰ the problem of the turbulent boundary layer[R].[S.l.]:Jet Propulsion Laboratory Report No.20-69,1953.
    [16]
    Settles G S,Williams D R,Baca B K,et al.Reattachment of a compressible turbulent free sheer layer[J].AIAA Journal,1982,20(1):60-67.
    [17]
    赵慧勇,雷波,乐嘉陵.非线性EASM在激波与湍流边界层相互作用中的数值应用[J].航空动力学报,2011,26(4):861-866. ZHAO Huiyong,LEI Bo,LE Jialing.Numerical application of nonlinear EASM model to the interaction between shock waves/turbulent boundary layer[J].Journal of Aerospace Power,2011,26(4):861-866.(in Chinese)
    [18]
    赵慧勇,雷波,乐嘉陵.非对称交叉激波和湍流边界层相互作用的数值研究[J].航空动力学报,2009,24(10):2184-2188. ZHAO Huiyong,LEI Bo,LE Jialing.Numerical investigation of interaction between asymmetric crossing shock waves/turbulent boundary layer[J].Journal of Aerospace Power,2009,24(10):2184-2188.(in Chinese)
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