Computational fluid dynamics prediction of Hyper-X stage separation aerodynamics

被引:16
作者
Buning, PG [1 ]
Wong, TC
Dilley, AD
Pao, JL
机构
[1] NASA Langley Res Ctr, Configurat Aerodynam Branch, Hampton, VA 23681 USA
[2] FDC NYMA Inc, Hyper X Program Off, Hampton, VA 23681 USA
关键词
Boosters (rocket) - Computational fluid dynamics - Computational methods - Database systems - Extrapolation - Flight dynamics - Hypersonic aerodynamics - Wind tunnels;
D O I
10.2514/2.3771
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
The NASA X-43 Hyper-X hypersonic research vehicle will be boosted to a Mach 7 flight test condition mounted on the nose of a Pegasus launch vehicle. The separation of the research vehicle from the Pegasus presents some unique aerodynamic problems, for which computational fluid dynamics has played a role in the analysis. We describe the use of several computational methods for investigating the aerodynamics of the research and launch vehicles in close proximity. Specifically addressed are unsteady effects, aerodynamic database extrapolation, and differences between wind-tunnel and flight environments.
引用
收藏
页码:820 / 827
页数:8
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