火箭冲压发动机掺混流场数值方法研究

NUMERICAL STUDY OF MIXING FLOWS IN A DUCTED ROCKET COMBUSTOR

鉴于火箭冲压发动机补燃室内呈现出复杂的三维化学反应流，传统方法对这一流场的数值分析所遇到的主要困难是求解椭圆型Ｎ－Ｓ方程组极为耗时而不利于工程应用，采用先进的块隐式法求解恒温掺混流场得到了很快的收敛速度，这一尝试为快速计算化学反应流打下了很好的基础。

The flowfield in the combustion chamber of ducted rocket is extremely complicated Because the main impediment of numerical analysis about reacting flows need a very long time in solving the elliptic Navier Stokes equations,a try was made to adopt an advanced block Implicit Algorithm in computing isothermal flow fields.The convergent speed was found very fast and this attempt laied a good foundation for computing reacting flows