咽式进气道设计工况下性能初步分析

Preliminary analysis of jaws inlet performance under design conditions

介绍了三维内收缩高超声速咽式进气道的设计方法,开发了相应的设计程序.在高度为30km,设计马赫数为5和攻角为0°工况下进行设计,使用CFD模拟技术,对设计方法和程序进行了验证.最后采用设计程序,考虑咽式进气道的设计参数,即流线追踪出口形状、基准流场压缩角和设计马赫数等,对比分析了其对咽式进气道设计工况下几何与气动性能的影响.结果表明：矩形出口宽高比接近2时,总长、润周面积等几何性能相比较小宽高比时更好.初步设计可以将压缩角配置在8°~12°范围内,且后压缩角小于前压缩角.

The design method of the three-dimensional inward turning hypersonic jaws inlet was introduced. Corresponding design codes were developed. Thereafter, a CFD technology was used to verify this method and the design codes with the generated jaws inlet model under the height of 30kin, design Mach number of 5 and attack angle of 0°, respectively. Finally, geometry and aerodynamic performances of jaws inlet under design conditions affected by the design parameters, such as the streamline tracing outlet profile, the compression angle set of base field and the design Mach number, were compared and analyzed. Result shows that compared with a low aspect ratio, the geometry performance will be better if the aspect ratio of rectangle-outlet approaches 2 with shorter total length and smaller surface area. Moreover, the compression angles should be set between 8° and 12° in preliminary design for relatively better performances, with the latter compression angle smaller than the former.