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分析了高超侧压式进气过第一、二溢流窗的溢流角随后掠角的变化规律，分析了溢流窗气流与主流相互作用而形成一道脱体曲面激波的原因，设计了侧压角为６°，后掠角３０°的直前缘及圆弧前缘两套高超侧压式进气道，在Ｍ５．３风洞中利用风洞壁面自然发展的附面层进行非均匀来流下进气道起动性能及总体性能试验，试验发现大量附面层吸入不仅对起动性能有重大影响，而且对总压恢复影响也极大。
The variation law of the sweep angle and the sweep angle of the overflow window of the first and second overflow windows are analyzed. The reason why the overflow window airflow interacts with the mainstream to form an offensive surface shock wave is analyzed. Lateral pressure angle of 6 °, the sweep angle of 30 ° straight front and arc front two sets of super-lateral pressure inlet, the wind tunnel in the M5.3 natural development of the surface layer of non-uniform use of non-uniform To start flowing into the inlet performance and overall performance test, the test found that a large number of inhalation of the overlay not only have a significant impact on the starting performance, but also greatly affect the total pressure recovery.