二维超声速混压式进气道的数值模拟

Numerical simulation of a two-dimensional mixed compression supersonic inlet

本文采用TVD格式求解二维可压非定常Euler方程组,对二维超声速混压式进气道进行了数值计算,首先模拟了后部压力对进气道的影响过程,当进气道的后部压力与入口压力的比值逐渐增加时,进气道内的正激波逐渐往前移动,当比值达到一个临界值,进气道将不起动。其次,通过对R52.1和R54.5两种进气道模型进行计算,对它们的总压恢复进行了对比。通过计算得到了喉道处曲线弧的曲率越大,进气道的总压损失越大,进气道也越难起动。

In this paper,numerical simulation of a two-dimensional mixed compression supersonic inlet is carried out by solving unsteady compressible Euler equations via a type of TVD scheme.First,the effect of inlet back pressure on flow was simulated,as the ratio of the back pressure and the inlet static pressure increasing,the normal shock moves upstream,and when it reaches a certain critical value,the inlet ‘unstarts’.Moreover,by simulating the model of R52.1 and R54.5,the total pressure recovery is discussed.It is demonstrated via simulations that,everything else being same,the geometries of ramp upstream of the throat that are associated with a curvature higher than a certain threshold,result in unstarting the intake and more total pressure loss.