超燃发动机激波增强混合的数值研究

Numerical Simulation of Shock Enhanced Fuel/Air Mixingin Scramjet Combustor

采用数值方法求解三维可压 Ｎ Ｓ方程，模拟了斜激波增强超声速氢／空气混合的过程。对不同强度激波混合增强的效率进行了比较。计算表明利用斜激波增强混合是一种行之有效的方法。

This paper describes a numerical study of fuel air mixing process of parallel hydrogen fuel injectors that are candidates for use in scramjet combustors.Weak plane oblique shock of variant angles were used to enhance the mixing process of the fuel.The finite volume method and LU SGS implicit method along with AUSM flux splitting scheme were used to solve the 3D Navier Stokes equations.The results show great mixing efficiency enhancement of this technique.