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中文摘要：
研究了抽吸位置和开槽形式对高超声速内收缩进气道涡流区和起动性能的影响.数值计算结果表明：在内收缩进气道下洗气流集中区域开槽对减小出口涡流区效果显著,在分离包内开槽可以以较小的流量损失来大幅提升进气道的起动性能.横纵向组合槽即T型槽的综合抽吸效率最高,相对原型进气道,设计点马赫数为6.0时在相对抽吸流量为1.01%时出口总压恢复系数提高了12.8%,畸变指数减小了37%;起动马赫数从5.2降至4.1,自起动马赫数由6.2降至4.8.
英文摘要：
The effect of bleeding positions and bleeding slot forms on the vortex region and starting performance of hypersonic inward turning inlet was researched. The numerical results indicate that bleeding slot in the downwash region of inward turning inlet can obviously reduce the vortex region on the exit plane, and the bleeding slot in the separation region can efficiently promote inlet starting performance with less mass flow losses. Combined T slot has the best comprehensive bleeding efficiency. Compared with the original inlet, when the relative bleeding mass flow rate is 1.01%, the total pressure recovery coefficient of exit plane increases 12.8%, distortion index decreases 37% on the design point Mach num ber 6.0. The starting Mach number decreases from 5.2 to 4.1, and self-starting Mach number decreases from 6.2 to 4.8.
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