IMECH-IR  > 高温气体动力学国家重点实验室
Alternative TitleNumerical investigation of Lorentz force control on hypersonic inlet boundary layer separation
苏纬仪; 张新宇; 张堃元
Source Publication推进技术
Other AbstractThe mechanisms of boundary layer separation caused by Shock /Boundary layer Interaction(SWBLI) in scramjet inlet and its control with Magnetohydrodynamics(MHD) were investigated numerically with a three dimensional CFD code,within which HLLE schemes,LU-SGS method,sst-kω turbulence model and multiblock structure grid were used.The results show that the numerical wall pressure agrees well with the experimental data,and the height of separation zone in the shoulder of scramjet inlet occupies 1/3 size of the throat height.With MHD accelerating the boundary layer,the separation in the scramjet inlet is eliminated,and the total pressure recovery coefficient is increased from 0.502 to 0.56,the flow field distortion parameter at the scramjet inlet throat zone is decreased by 18.6%.
Keyword高超声速进气道 Mhd流动控制 激波-边界层相互作用 边界层分离 数值仿真
Subject Area力学
Indexed ByEI ; CSCD
Funding Organization国家自然科学基金资助(90916029)
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Document Type期刊论文
Corresponding Author苏纬仪
Recommended Citation
GB/T 7714
苏纬仪,张新宇,张堃元. 洛仑兹力控制高超声速进气道边界层分离的数值模拟[J]. 推进技术,2011,32(1):36-41.
APA 苏纬仪,张新宇,&张堃元.(2011).洛仑兹力控制高超声速进气道边界层分离的数值模拟.推进技术,32(1),36-41.
MLA 苏纬仪,et al."洛仑兹力控制高超声速进气道边界层分离的数值模拟".推进技术 32.1(2011):36-41.
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