HYPERSONIC MODEL TESTING IN A SHOCK TUNNEL

被引：4

作者：

OLIVIER, H ^{[1
]}

GRONIG, H ^{[1
]}

LEBOZEC, A ^{[1
]}

机构：

[1] DASSAULT AVIAT,F-78141 VELIZY VILLACOUBL,FRANCE

来源：

AIAA JOURNAL | 1995年 / 33卷 / 02期

关键词：

Hypersonic aerodynamics;

D O I：

10.2514/3.12429

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

A shock tunnel is used to perform tests at hypersonic flow conditions including weak real gas effects. Pressure and heat nux distributions are measured around typical re-entry configurations. From these data c(p) values and Stanton numbers are deduced. For constant Mach and Reynolds number the experimental results achieved indicate a strong influence of the total temperature on the Stanton number distribution. For the results presented this behavior is mainly based on entropy layer and viscous interaction effects. A correlation function which takes into account these effects correlates the Stanton numbers achieved for different now conditions and in different wind tunnels fairly well.

引用

页码：262 / 265

页数：4

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