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采用数值模拟和风洞试验的方法,对吸气式高超声速飞行器盲腔状态的流动特性进行了研究。采用“双时间步”方法进行了内外流一体化的非定常数值模拟,利用彩色纹影系统对高超声速飞行器前体流场进行显示,并采用动态压力传感器测得了飞行器内流道的壁面压力随时间的变化。结果表明:盲腔构型在高超声速飞行中会出现周期性的激波振荡现象。数值模拟所得流场变化特征、内流道壁面压力振荡周期和壁面压力变化趋势与试验结果吻合良好。
The numerical simulation and wind tunnel test methods were used to study the flow characteristics of blind cavity in aspirated hypersonic vehicles. The unsteady internal and external flow numerical simulation is carried out using the “double time step” method. The flow field of the precursor of the hypersonic vehicle is displayed by using the color image system. The dynamic pressure sensor is used to measure the wall of the flow passage in the aircraft Pressure changes over time. The results show that the periodic cavity oscillation appears in the blind cavity configuration during hypersonic flight. The characteristics of the flow field obtained by numerical simulation are in good agreement with the experimental results.