高超声速二元进气道顶板移动变几何方案数值模拟

Numerical Simulation of a Variable Geometry Hypersonic 2D Inlet Designed with Compressible Ramp Movable

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。

This paper investigates a variable geometry design with partially compressible ramp movable to simulate a hy- personic two-dimensional （2D） inlet working from Mach number Ma = 4-6. The inlet self-starting performance at Ma = 4 and the adjusting method from Ma = 4 to Ma = 6 are studied by means of numerical simulation. The results show that the variable geometry inlet self-start can be realized at Ma = 3.7, and the discharge capacity of the adaptive bleed slot formed by the variable geometry is below 2%. When the adaptive bleed slot is closed after starting, the mass flow rate reaches 0.77 at Ma =4. This design enables the inlet to possess a high mass flow rate and good performance during the whole working range, and the adjusting method is practical and feasible.