逃逸飞行器喷流影响试验研究

Experimental Investigation of Jet Effect ofSpaceshuttle with Multinozzle on Head

本文介绍了在跨超声速风洞中进行的逃逸飞行器模型气动特性、载荷分布及流场结构试验研究，提供了Ｍ＝０．６～４．０，α＝－２°～２０°范围内的试验结果。试验结果和流动图象表明：由逃逸飞行器头部喷射出的喷流严重影响逃逸飞行器的气动特性和载荷分布。

The aerodynamic characteristics of escape vehicles with its load distributions and flow structures were explored experimentally in a transonic/supersonic wind tunnel.This paper presents the results obtained at M=0.6～4.0 and α=-2°～20°.The results and images show that jet issuing from the head of escape vehicles plays a quite important role and changes its aerodynamic characteristics and load distributions greatly.