北京航空航天大学学报 ›› 2013, Vol. 39 ›› Issue (5): 590-594.

• 论文 • 上一篇    下一篇

DES方法对返回舱气动热环境数值模拟

刘佳1, 阎超1, 赵瑞1, 蒋海军2   

  1. 1. 北京航空航天大学国家计算流体力学实验室, 北京 100191;
    2. 北京临近空间飞行器系统工程研究所空间物理重点实验室, 北京 100076
  • 收稿日期:2012-05-07 修回日期:2012-11-16 出版日期:2013-05-31 发布日期:2013-05-22
  • 基金资助:
    国家973计划资助项目(2009CB724104)

Simulation of re-entry capsule thermodynamics environment by DES method

Liu Jia1, Yan Chao1, Zhao Rui1, Jiang Haijun2   

  1. 1. National Key Lab of Computational Fluid Dynamics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
    2. Science and Technology on Space Physics Laboratory, Beijing Institute Nearspace Vehicle's System Engineering, Beijing 100076, China
  • Received:2012-05-07 Revised:2012-11-16 Online:2013-05-31 Published:2013-05-22

摘要: 脱体涡模拟方法(DES,Detached Eddy Simulation)由于结合了湍流模型(RNAS,Reynolds Averaged Navier-Stokes)和大涡模拟(LES,Large Eddy Simulation)两者各自优势,是模拟非定常大分离流动的有效方法.采用基于SA(Spalart-Allmaras)湍流模型的DES方法,对高超声速返回舱外形进行数值模拟,计算所得的返回舱表面压力及热流分布与实验结果吻合,证实了DES方法的优越性.最后,在DES方法中加入可压缩修正,结果证实在高超声速流动中,可压缩修正方法在一定程度上能够提高原始模型的预测性能.

Abstract: Detached eddy simulation (DES) is an effective numerical simulation method for unsteady separated flow since it combines the advantages of both Reynolds averaged Navier-Stokes(RANS) and large eddy simulation (LES) methods. Spalart-Allmaras(SA) based DES method is used for the re-entry case under hypersonic condition. Comparison of the pressure and heat flux distributions shows that the numerical results agree well with the experiment data and thus validate the advantages of the DES method. Compressibility corrections were added in the original SA turbulent model. In the hypersonic flow characterization, the introduction of compressibility corrections can better the original turbulent method's simulation capability.

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