DES方法对返回舱气动热环境数值模拟

刘佳; 阎超; 赵瑞; 蒋海军

DES方法对返回舱气动热环境数值模拟

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

基金项目: 国家973计划资助项目(2009CB724104)

详细信息

中图分类号: V211.3
计量
- 文章访问数: 1752
- HTML全文浏览量: 148
- PDF下载量: 784
- 被引次数: 0
出版历程
- 收稿日期: 2012-05-07
- 修回日期: 2012-11-16
- 网络出版日期: 2013-05-31

Simulation of re-entry capsule thermodynamics environment by DES method

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

摘要

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.
- 脱体涡模拟方法 /
- 可压缩修正 /
- 湍流模型 /
- 气动热 /
- 返回舱
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.
- detached eddy simulation(DES) /
- compressibility correction /
- turbulent model /
- heat flux /
- re-entry

HTML全文

参考文献(9)

[1]	赵梦熊.载人飞船空气动力学[M].北京:国防工业出版社,2000 Zhao Mengxiong.Manned spacecraft aerodynamics[M].Beijing:National Defense Industry Press,2000(in Chinese)
[2]	王安龄,桂业伟,耿湘人,等.飞船返回舱气动热及烧蚀防热的不确定性初步研究[J].工程热物理学报,2005,26(5):862-864 Wang Anling,Gui Yewei,Geng Xiangren,et al.Study on uncertainty bands of aerodynamically heating rate and material performance in thermal protection for spaceship capsule[J].Journal of Engineering Thermophysics,2005,26(5):862-864 (in Chinese)
[3]	赵梦熊.载人飞船返回舱的气动热流率分布[J].气动实验与测量控制,1996,10(1):1-7 Zhao Mengxiong.The aerodynamic heating distribution of capsule type re-entry vehicle[J].Aerodynamic Experiment and Measurement & Control,1996,10(1):1-7(in Chinese)
[4]	Strelets M.Detached eddy simulation of massively separated flow[R].AIAA 2001-0879,2001
[5]	Spalart P R,Allmaras S R.A one-equation turbulence model for aerodynamic flows[R].AIAA 92-0439,1992
[6]	Wilcox D C.Turbulence modeling for CFD[M].California:DCW Industries,2006
[7]	Kedia K S,Sinha K.Effect of compressibility corrections to turbulence models applied to a hypersonic re-entry configuration[R].NCFMFP 2006-1221,2006
[8]	Shur M,Strelets M,Zaikov L,et al.Comparative numerical testing of one-and two-equation turbulence models for flows with separation and Reattachment[R].AIAA 95-0863,1995
[9]	Barnhardt M,Candler G V.CFD analysis of CUBRC base flow experiments[R].AIAA 2010-1250,2010