FLOW OVER AN ALL-BODY HYPERSONIC AIRCRAFT - EXPERIMENT AND COMPUTATION

被引:17
作者
LOCKMAN, WK
LAWRENCE, SL
CLEARY, JW
机构
[1] NASA,AMES RES CTR,APPL COMPUTAT FLUIDS BRANCH,MOFFETT FIELD,CA 94035
[2] ELORET INST,SUNNYVALE,CA 94087
关键词
D O I
10.2514/3.26308
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
The objective of the present investigation is to establish a benchmark experimental data base for a generic hypersonic vehicle shape for validation and/or calibration of advanced computational fluid dynamics computer codes. This paper includes results from the comprehensive lest program conducted in the NASA Ames 3.5-ft Hypersonic Wind Tunnel for a generic all-body hypersonic aircraft model. Experimental and computational results on flow visualization, surface pressures, surface convective heat transfer, and pitot-pressure flowfield surveys are presented. Comparisons of the experimental results with computational results from an upwind parabolized Navier-Stokes code developed at NASA Ames demonstrate the capabilities of this code.
引用
收藏
页码:7 / 15
页数:9
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