基于特征线理论的超声速进气道压缩面设计研究

摘要

A computation program was developed based on Method of Characteristic (MOC), with which the supersonic inlet compression surface was designed according to the prescribed parameter change law along the compression surface.The influence of pressure gradient and Mach number gradient on inlet performance was studied and compression surface was designed overall considering the two laws of compression.It was showed that efficiency of the design of supersonic inlet compression surface was greatly increased with the use of the MOC method.Strategy design was conducted, through which the compression surface with high capability was obtained.The pressure gradient in the rear section was greatly decreased and the outlet parameter distribution was more even if the compression law of Mach number cubic curve was adopted, the pressure gradient would also be reduced and better compression results would be gained.%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口截面的总压恢复系数下降.