亚声速埋入式进气道性能回归分析

Regression analysis on performance of a subsonic submerged inlet

根据某埋入式进气道试验数据建立了计算埋入式亚声速进气道总压恢复系数的经验公式,表现为关于马赫数、流量系数、攻角、侧滑角的函数。该经验公式可用于弹用发动机稳态、起动、加速过程的计算和导弹与发动机一体化设计的数值仿真模型,从而提高发动机性能数值仿真的准确性。

The relevance functions between total pressure recover coefficient and the parameters （Mach number, angle of attack, flow coefficient, angle of sideslip） for subsonic submerged inlet in turbojet and turbofan engine were investigated. This experiential formula can be used in simulating steady condition, startup, acceleration work process and integrated design of cruise missile and turbofan engine so as to improve the accuracy of ID engine performance computation.