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针对一种工作于马赫数Ma=4～6范围内的高超声速二元进气道,探索了一种进气道部分压缩顶板可移动的简单变几何方案,利用数值模拟研究了接力点变几何进气道的自起动性能和Ma=4～6的调节方法。结果表明:部分压缩顶板可移动简单变几何进气道方案在Ma=3.7能够实现自起动;变几何所形成的自适应放气槽放气量很小,最大放气量在2%以内,关闭自适应放气槽接力点Ma=4流量系数达到0.77;在整个工作范围内流量系数较高、总体性能较优,该变几何方案的调节方法是切实可用的。
Aiming at a hypersonic binary inlet with a Mach number of Ma = 4 ~ 6, a simple and variable geometry scheme of partially movable roof of the inlet is explored. By using numerical simulation, Intake of the self-starting performance and Ma = 4 ~ 6 adjustment method. The results show that the scheme of partially variable roof movable simple variable geometry inlet can be self-starting at Ma = 3.7. The deflated geometry of the deflated aeration tank is very small with the maximum deflated volume less than 2% Deflation tank relay point Ma = 4 flow coefficient of 0.77; in the entire operating range of the flow coefficient is higher, the overall performance is better, the variable geometry adjustment method is practical.