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首先分析了进气道等效圆波导中发动机等效“半球＋ 平面扇形金属叶片”终端的不连续性，根据电磁场互易定理和物理光学法（ Ｐ Ｏ） 计算了这种终端的反射系数；然后利用“传输模式叠加法”计算了进气道的雷达散截面（ Ｒ Ｃ Ｓ） 。计算结果与实验结果比较吻合，优于文献给出的计算结果。这种方法采用模式迭加求和，避免了普通模式法需进行大型矩阵计算以及对计算机内存的过高要求。
Firstly, the discontinuity of the equivalent “hemispherical + planar fan-shaped metal blade” in the equivalent circular waveguide of the air inlet is analyzed. The reflection coefficient of this terminal is calculated according to the reciprocity theorem of electromagnetic field and the physical optics (P O) Then the radar cross-section (R C S) of the intake port is calculated by using “transmission mode superposition method”. The calculated results are in good agreement with the experimental ones, which are better than the ones given in the literature. This approach uses summation of patterns to avoid the need for large-scale matrix calculations and excessive demands on computer memory for normal mode methods.