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首先对澳大利亚HyShot计划进气道模型进行了数值模拟,得到了设计状态及非设计状态下的流场特征,以及进气道性能随来流马赫数的变化规律.根据分析,提出了在二元高超声速进气道内压段开设溢流槽的设计思路,设计了工作马赫数范围为4.0～6.0的二元高超声速进气道,并给出了通过抬高或降低原设计槽口高度得到的两种新的开槽方案进气道的物理模型.通过数值模拟,结果表明:溢流槽有效改善了进气道的性能,拓宽了进气道的工作范围,槽口高度的不同对进气道性能有相当大的影响.
Firstly, the inlet model of HyShot project in Australia was numerically simulated, and the characteristics of flow field under design state and non-design state were obtained, and the variation of inlet port performance with Mach number was analyzed.According to the analysis, Hypersonic inlet section of the internal pressure section of the design of overflow groove design, the design of the Mach number range of 4.0 to 6.0 binary hypersonic inlet, and given by raising or lowering the original design of the notch height obtained The results show that the overflow groove effectively improves the performance of the air inlet and widens the working range of the air inlet, and the difference of the height of the notch affects the intake air Road performance has a considerable impact.