高超声速飞行器进气道压缩面逆向设计方法

针对高超声速飞行器进气道压缩面问题,首先研究了激波理论的逆向算法,以此为基础提出了进气道的等强度和等熵压缩面的逆向设计方法,并采用此方法设计了以进气道出口气流参数为设计参数的高超声速飞行器进气道压缩面,然后对两种压缩面进行了性能分析和数值仿真.结果表明:通过逆向设计方法设计进气道压缩面是可行的,其相对于传统方法耗时大大减少;理论计算表明相同设计条件下两压缩面几何参数基本一致,而来流参数也基本不变,设计点下等熵压缩面总压恢复系数高出等强度压缩面6.3%.数值仿真验证了该方法的可行性并研究了非设计状态下两种压缩面的各项性能参数,同时对比了不同马赫数下进气道内部波系分布和气流均匀性. 

Reverse design method of hypersonic aircraft inlet compression surface

For the problem of hypersonic aircraft inlet compression surface, a reverse design method of constant intensity and isentropic compression surface was proposed firstly based on the investigation of the reverse algorithm of the shock wave theory, then inlet compression surfaces of hypersonic flight vehicle were designed using this method with the flow parameters of inlet exit, next performance analysis and numerical simulation were conducted. The results show that: the reverse design method is effective and time-saving as compared with the traditional method. Theoretical calculation shows that both the geometry parameters and the incoming flow parameters of two compression surfaces are most consistent, the total pressure recovery coefficient of the isentropic compression increases by 6.3% to the constant intensity compression at designed point. The numerical simulation has verified the effectiveness of the proposed method and studied the performance parameters of two compression surfaces under off-design condition, while comparing the internal wave system distribution and airflow uniformity of the inlets under different Mach numbers.