通过理论分析和风洞实验，对工作在前体附面层内的侧压式进气道，研究了等激波压比和等溢流角前提下侧压缩面的设计方法，分析了６种不同的侧压缩型面在４种来流附面层中，波后压力沿高度的变化规律和溢流角的变化规律。研究发现，采用部分圆弧加直线为前缘。四次曲线为斜面后缘型线的侧压缩面，在４种非均匀来流下的特性较好。马赫５．３的非均匀流风洞实验结果表明，等压比和等溢流角设计的侧压式进气道较通常的直前缘侧压式进气道，在非均匀来流中喉道截面马赫数分布均匀度好，总压恢复略高 Through the theoretical analysis and wind tunnel experiment, the design method of the compression surface under the premise of equal shock pressure ratio and equal overflow angle was studied for the side-pressure inlet port working in the precursor overburden. Six kinds of The variation of wave pressure along the height and the variation of overflow angle in four different types of surface flow were observed for different side compression profiles. The study found that the use of some arc plus straight line as the leading edge. The quadratic curve is the lateral compression surface of the trailing edge line, which is better under the four kinds of non-uniform flow. The results of the Mach-5.3 non-uniform flow wind tunnel experiment show that the side-pressure inlet with the equal pressure ratio and the equal-relief angle has a lower pressure than the usual straight-ahead side pressure inlet, Section Mach distribution uniformity, total pressure recovery slightly higher