复杂外形跨大气层飞行器模型气动热试验研究

Study of aero-heating characteristics for trans-atmospheric vehicle

针对复杂外形跨大气层飞行器,在2m激波风洞中开展了气动热试验研究,试验条件为:M∞≈10,迎角α=0°,10°,20°,30°,40°。通过试验给出了飞行器模型表面沿迎风中心线、背风中心线、机身四个截面、机翼上下表面、翼前缘、尾翼表面的热流分布试验结果。同时,发展了有限体积法的三维可压缩N-S方程解算器,建立了气动热数值计算方法,并根据风洞试验条件进行了气动热数值计算,与试验结果进行了分析比较。综合试验和数值计算结果,对跨大气层飞行器的气动热特性进行了分析研究,给出了表面热流的分布特征和随迎角的变化规律。

An investigation of aero-heating was completed in shock tunnel for trans-atmospheric vehicle at the flow field conditions ： M∞ ≈ 10, and the attack angles α = 0°, 10°, 20°, 30°, 40°. Experimental results include heat transfer distributions along windward centerline, leeward centerline, four sections of body, upper and lower surfaces of wing, wing edge, tail surface. At the same time, the numerical calculation method of aero-heating was developed with finite-volume N-S solver. Then the numerical calculation of aero-heating was taken under the test conditions. Analysis was carried out through the comparison of test results with computational results. At last, aero-heating characteristics for trans-atmospheric vehicle was analyzed, and the aeroheating characteristics on the surface and the regularity with attack angle were obtained.