Academic optimal design method of the 2-D and axisymmetric external-compression supersonic inlet were presented. After design, the performance of two different types inlet are calculated and compared in the design point Ma =2. 5, H = 10 km. The results show that, in the same condition, 2-D inlet have higher total pressure recovery coefficient but the outlet flow of axisymmetric inlet is uniform and has a smaller distortion coefficient, a lower Mach number. The result could provide references for the choice of the type of supersonic inlet.%给出了二元和轴对称两种不同结构形式的进气道进行理论最优设计方法；并以飞行马赫数Ma =2.5,高度H=10km为设计点,计算和比较了两种进气道的性能.结果表明在相同情况下,二元进气道具有相对较高的总压恢复系数,但轴对称进气道出口的气流较均匀、畸变较小,并且马赫数较低.这一结果可为冲压发动机进气道结构形式的选择提供理论依据.
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