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针对一种采用新型压升规律的曲面压缩面所设计的高超弯曲激波二维进气道,利用数值模拟方法研究了6种不同长度平板发展而来的非均匀流对其性能参数的影响,并和两种常规二维进气道吞非均匀来流的能力进行了比较,着重对比了设计Ma数下三种不同压缩形式进气道喉道截面的流场畸变程度。数值模拟结果表明,采用新型压升规律的高超弯曲激波二维进气道性能受来流气流不均匀性的影响较小,且喉道截面的流场畸变指数小,对非均匀来流具有一定的校正作用。
Aiming at a two-dimensional hypersonic shock inlet designed by a new type of surface compression plane, the influence of non-uniform flow from six different length plates on its performance parameters is studied by using numerical simulation method. Compared with the ability of two conventional two-dimensional intake ports to swallow non-uniform flow, the degree of distortion of the flow field in the throat section of the inlet of the three different compression modes with different design numbers is emphatically compared. The results of numerical simulation show that the performance of the two-dimensional inlet of the hypersonic bending shock wave with the new pressure rise law is less affected by the inhomogeneity of the incoming airflow and the flow field distortion index of the throat section is small. A certain role of correction.