固体火箭冲压发动机进气道三维数值模拟

Three dimension numerical simulation on air inlet of solid ducted rocket

基于RANS平均的N-S方程、标准k-ε双方程湍流模型,利用FLUENT软件对某型固体火箭冲压发动机进气道内外流场进行了三维数值模拟.研究了不同马赫数下进气道前体、入口、进气道出口流场和流动特性;考虑了弹体,缩比,网格划分对进气道流场出口参数的影响.模拟结果表明:随着飞行马赫数的增加,由前缘点产生的激波逐渐靠近弹体,进气道内部总压恢复系数降低,在进气道出口处压力比较高,出口流场基本均匀.

Based on the N-S equation,standard k-ε turbulence model,the FI.UENT was used to simulate the kind of air inlet of solid ducted rocket. The paper researched the front , the lip, the interior and the back of the air inlet at vary Mach number. The simulation of results indicated that with Mach number increased and the total pressure recovery coefficient decreased. The flow is complex in the interior of air inlet, pressure is relatively high at exit of air inlet but the outflow is basically fluent and uniformity.