Experimental study on thermal protection system by opposing jet in supersonic flow

被引：137

作者：

Hayashi, K ^{[1
]}

Aso, S ^{[1
]}

Tani, Y ^{[1
]}

机构：

[1] Kyushu Univ, Dept Aeronaut & Astronaut, Higashi Ku, Fukuoka 8128581, Japan

来源：

JOURNAL OF SPACECRAFT AND ROCKETS | 2006年 / 43卷 / 01期

关键词：

D O I：

10.2514/1.15332

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The reduction of aerodynamic heating by opposing jet was experimentally investigated. Geometric ratio of diameters and Mach numbers were fixed, and the flow stability was determined by the total pressure ratio of freestream to opposing jet. It was observed that the reduction of aerodynamic heating caused by the opposing jet proved to be quiet effective at the nose of the blunt body. As the pressure ratio is increased, the heat flux decreases over the model surface, and remarkable reduction of aerodynamic heating was observed in nose regions at high pressure rate.

引用

页码：233 / 236

页数：4

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