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首页> 外文会议>56th International Astronautical Congress 2005 vol.7 >DESIGNING AND AERODYNAMIC PERFORMANCE OF THE COMBINED-CYCLE ENGINE INLET IN A HYPERSONIC FLOW
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DESIGNING AND AERODYNAMIC PERFORMANCE OF THE COMBINED-CYCLE ENGINE INLET IN A HYPERSONIC FLOW

机译：超声速复合循环发动机进气口的设计及气动性能

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New designs of the inlet of a combined-cycle engine were explored to improve the aerodynamic characteristics. Three modifications to the prototype design were actually examined in CFD and hypersonic experiments. Prom the CFD analysis, it was found that the ramp shock was deformed and created an additional spillage, due to the interaction with sidewall-originated waves. The pressure distributions on the top wall, obtained in the experiments, showed similar profile with the CFD data when the incoming boundary layer was thin. The capture ratio was evaluated in the experiments but it showed rather low value than expected. The reasons were again the ramp shock deformation and the lack of measuring points. Within the three models, "double stage" ramp model showed the best performance.
机译：探索了联合循环发动机进气口的新设计，以改善空气动力学特性。实际上，在CFD和高超声速实验中对原型设计进行了三处修改。在进行CFD分析时，发现由于与侧壁起源的波相互作用，斜坡冲击变形并产生了额外的溢出物。在实验中获得的顶壁上的压力分布在进入边界层较薄时显示出与CFD数据相似的轮廓。在实验中评估了捕获率，但是它显示出比预期低的值。原因再次是坡道冲击变形和缺乏测量点。在这三个模型中，“双级”斜坡模型表现出最佳性能。

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