摘要
本文介绍了应用主气流引射,在驻室开缝调节驻室压力的新方法,取代了用引射器引射,并调节驻室压力的传统方法,其结果扩大了调节压力比的范围,提高了调节精度,扩大了 FD-02 风洞喷管出口面积,实现了在小风洞中做大模型实验的目的。通过Ⅰ号战术导弹的燃气舵风洞气动力实验证明,气动力的测量精度提高两倍,力矩的测量精度提高3.34倍到4.0倍,而每次吹风所消耗的气源流量比原来的要减少一半以上。
This paper describes a new method of regulating thepressure ratio in a test chamber by gapping to replace the traditionalmethod that used a injector to inject and regulate pressure ratio of thetest chamber.The main advantages of this technique are to expand therange of regulating test chamber pressure ratio;to enhance the accuracyof regulating test chamber pressure ratio;to expand the exit area of thenozzle of FD-02wind tunnel;and to realize the propose of operating alarge model in a small wind tunnel.The aerodynamic test performed in FD-02 wind tunnel using the gashelm models of NO.1 tactical missile proved the following results.The accuracy of the force measurement increased twice;the accuracyof the moment measurement increased 3.34 to 4.0 times,while the con-sumption of the air supply decreased more than 50% compared to theorignal consumption.
关键词
超声速风洞
驻室
压力调节
射流式
test chamber
pressure ratio
injector
regulatingthe pressure by gapping
