工作在前体附面层内的高超侧壁压缩进气道，来流的非均匀性应该是进气道设计的一个重要依据。按经典的附面层理论和等溢流角设计准则设计了侧壁压缩角为６°，前缘型线为圆弧的变后掠角高超侧压式进气道模型，在Ｍａ５．３／Ｍａ４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性能试验。试验发现，在相同的来流附面层条件下，圆弧前缘进气道相对于直前缘进气道喉道处的压力畸变小、进气道总压恢复高。 Work in the precursor attached to the superficial sidewall compression inlet, non-uniform flow should be an important basis for the design of the inlet. Based on the classical theory of surface layer and the design criterion of equal overflow angle, a highly variable over-sweep pressure inlet model with sidewall compression angle of 6 ° and a leading edge line of arc is designed. Ma4 wind tunnel using the natural development of wind tunnel surface layer of non-uniform flow into the inlet performance test. The experimental results show that under the same flow boundary conditions, the pressure distortion at the inlet of the circular arc inlet is smaller than that of the straight inlet air inlet throat, and the total inlet pressure is restored.