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采用一维气动分析和三维流场数值模拟两种方法,对超声速二元进气道的性能进行了研究。研究结果表明,超声速进气道侧向膨胀对进气道性能影响显著,侧向膨胀使进气道喉部马赫数增大,扩张段正激波强度增大,进气道总压恢复系数和流量捕获系数都减小。
Two-dimensional aerodynamic analysis and three-dimensional flow field numerical simulation are used to study the performance of supersonic dual inlet. The results show that the lateral expansion of the supersonic inlet has a significant effect on the inlet performance. The lateral expansion causes the Mach number of the inlet to increase, the positive shock intensity of the expansion increases, the total pressure recovery coefficient of the inlet and Flow capture coefficient is reduced.