超音速射流气膜冷却效果的试验研究

Experimental Study on Film Cooling with Supersonic Injection

以二维平板模拟高速导弹头罩上的探测窗口，用电加温产生的热气流模拟导弹飞行时的气动加热，对采用气膜冷却控制导弹探测窗口温度的效果及规律进行了研究。着重探讨了气膜冷却临界长度ＬＣ与气膜冷却有效度η随射流缝高ｓ、喷射率λ及主射流夹角α等参数的变化规律，并总结出一个相关参数及一些经验公式。研究结果与国外有关文献基本一致。

An experiment using a two dimensional plate wall model of an interceptor forebody configuation is studied to determine the effectiveness of film cooling on temperature control of an infrared window during the high speed flight. The effect of slot height, mass flow ratio, angle of freestream and injection coolant, on the cooling length and cooling effectness, is emphatically studied. In addition, a correlation parameter is obtained. The test results are a general in agreement with the reference date of tunnel at Mach 8.