Abstract: A time dependent, implicit, finite volume, lower upper numerical method was used to solve the three dimensional compressible Reynolds averaged Navier Stokes equations and simulate the complicated flow phenomena such as shock trains and vortex structures in rectangular isolator caused by the shock wave/boundary layer interaction. Numerical solutions of the interaction in rectangular isolator were obtained, and the numerical results were compared with experimental data.

Key words: Supersonic combnstion ramjet engine;Isolator;Finite volume method;Shock wave effect;Numerical simulation

摘要： 针对三维矩形等截面隔离段中由激波 附面层干扰诱导的复杂流场 ,采用有限体积方法、OC TVD格式结合B L代数湍流模型隐式求解了三维雷诺平均N S方程 ,数值模拟了三维流场内复杂的激波串和旋涡结构。计算结果表明所采用的数值方法能够很好地捕捉隔离段内流场的复杂流动现象。

关键词: 超声速燃烧冲压发动机;隔离器;有限体积法;激波效应;数值仿真