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本文通过数值分析和风洞实验 ,在马赫数 5.3的非均匀来流条件下 ,研究改变二元内外压四波系进气道第一压缩面的型面设计 ,对进气道总体性能的影响。研究结果表明 ,与双平面斜楔的内外压四波系基准进气道相比 ,在非均匀来流中 ,采用小进口角 ,大出口角凹型面作为第一压缩面的进气道 ,其喉道截面总压恢复要高 0 .0 1～ 0 .0 2 4。总压畸变平均低 1 0 %左右 ,证明调整第一压缩面型面是改善这类工作在前体边界层内的进气道性能的有效方法。
In this paper, by numerical analysis and wind tunnel experiment, under the non-uniform flow conditions of Mach number 5.3, the effect of changing the design of the profile of the first compression face of the quadrupole inlet of dual internal pressure and external pressure on the overall inlet performance . The results show that in the non-uniform flow, compared with the dual-plane wedges, the inlet of the first compression plane is the concave face with small entrance angle and large exit angle. Throat section total pressure recovery to be high 0 .0 1 ~ 0 .0 2 4. The average total pressure distortion is about 10% lower on average, proving that adjusting the first compression surface is an effective way to improve the inlet performance of such work in the precursor boundary layer.