冲压发动机外压式二元进气道优化设计与流场分析

介绍了冲压发动机外压式二元进气道设计方法，基于ModelCenter软件平台，使用遗传算法对外压段压缩楔角进行了优化设计，得到最佳的总压恢复系数；并使用有限体积法、 SST湍流模型对所设计的二元外压式进气道设计状态和非设计状态进行了数值模拟，分析了出口反压及来流马赫数对进气道流场的影响。结果表明，随着反压的增加，进气道结尾正激波位置前移，进气道总压恢复系数增加，出口马赫数减小；随着来流马赫数的增加，进气道总压恢复系数显著降低。

Design and Analysis of External-Compression Supersonic Inlet for Ram Engines

In this paper, the design method of 2-D supersonic inlet was introduced, and in order to the optimal total pressure recovery coefficient, base on the ModelCenter software platform, the genetic algorithms was used to optimize the wedge angles of external-compression section of supersonic inlet; The flow field of inlet in design and off-design condition was simulated by using the finite volume method, SST turbulence model. The effect of back pressure and flight Mach number on inlet flow fields were also analyzed and discussed. It is indicated that with the back pressure increases, the normal shock of inlet moves forward, and the total pressure recovery coefficient increases and the Mach number decreases; while with the flight Mach number increases, the total pressure recovery coefficient dramatically decreases.