高超声速双模块内转式进气道的流动特性研究-Part I： 设计状态

本文通过特征线法设计了基于多道激波+等熵压缩波的基准流场，在此基础上通过流线追踪法设计了双模块内转式进气道。通过数值仿真和风洞试验相结合的方法，获得了内转式进气道的内外流特性。研究结果表明：在内转进气道最大半径对应的角区位置存在大量的边界层堆积，受第二道激波/边界层干扰，在激波根部卷起锥形旋涡；在内转式进气道内部，唇罩激波和管道边界层干扰显著，管道内存在自唇罩指向压缩面的强周向压力梯度，从而诱导管道内边界层均往一处汇聚，卷起大尺度流向涡。仿真和试验结果表明在来流马赫数5.74，攻角0度状态下，进气道气动性能优良，出口总压恢复系数系数达到0.58，最大抗反压为112倍。

Flowfield of Hypersonic Bimodule Inward-Turning Inlet-Part I: Design Point

In this paper, a basic flowfield contained multiple shocks and isentropic compression waves are designed by the method of characteristics, bi-module inward-turning inlets are then designed. The external-internal flowfield features are investigated numerically and experimentally. The results indicate that plentiful of boundary layer is accumulated at the corner with the largest radius of the inlet leading edge. Due to the second shock/boundary layer interaction, conical vortices are generated under the shock. In the internal duct, apparent cowl shock/duct boundary layer interactions are encountered, a strong circumferential pressure gradient, which originates from the cowl and points to the ramp, is induced. The pressure gradient drives the duct boundary layer to converge which is wrapped into a large scale vortex further. The numerical and experimental results demonstrate that the inlet has favorable aerodynamic performances with the total-pressure recovery coefficient of 0.58 and the maximum sustainable pressure ratio of 112 under the incoming Mach number of 5.74 and attack angle of 0 degree.