【摘 要】
：
基于有旋特征线理论开发了特征线程序,通过指定压缩面沿程参数变化规律,得到了满足指定压缩规律的进气道前体压缩面。对不同压缩规律的影响进行了分析,并进行了策略选择。分
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基于有旋特征线理论开发了特征线程序,通过指定压缩面沿程参数变化规律,得到了满足指定压缩规律的进气道前体压缩面。对不同压缩规律的影响进行了分析,并进行了策略选择。分析结果表明:特征线法可高效指导超声速进气道压缩面设计;采用分段设计策略可得到高总压恢复系数和高增压比的压缩面,同时后段压力梯度大幅下降,有利于附面层稳定,出口截面参数分布更为均匀;采用马赫数三次曲线压缩规律也可以降低出口的压力梯度,提高三次曲线拐点处的马赫数梯度可以增大压缩效果,但如果预设的出口壁面马赫数较低,则增大拐点处的马赫数梯度可能会使得出
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