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对一种组合发动机变几何进气道各马赫数下不同几何形状的三维流场进行了数值模拟.研究了不同马赫数时进气道的流场特征及气动性能.结果表明:随着来流马赫数的减小,外压段的超声溢流不断增大,进气道的流量系数不断减小;第一道内压缩波及其反射点位置对组织管道内的流场有着非常重要的作用;当有反压作用时,会在扩张段内形成激波串,激波串的形状和位置与来流马赫数、反压大小及管道内的流动有关.研究结果对类似进气道的几何调节方式有一定的指导意义.
A three-dimensional flow field with different geometries at different Mach numbers of a combined engine inlet was numerically simulated. The flow field characteristics and aerodynamic performance of the inlet at different Mach numbers were studied. The results show that with the flow The decrease of Mach number, the increase of ultrasonic overflow in the external pressure section and the decrease of the flow coefficient of the inlet duct, the first internal compression wave and its reflection point position play a very important role in the flow field in the tissue pipeline. When a back pressure is applied, a shock wave string will be formed in the expansion segment. The shape and position of the shock wave train are related to Mach Mach number, backpressure magnitude and flow in the pipeline. The way has a certain guiding significance.