Abstract: A numerical simulation code was developed for calculation of the 2 D flow field of supersonic combustion. The two dimensional, time dependent Navier Stokes equations were solved using flux split method and MacCormack′s explicit predictor corrector scheme of two order precision with the algebraic B L eddy model corrected by the wall function and Prandtl mixing length model The experimental conditions of supersonic combustion of fuel rich hot gas was simulated using C 2H 4 O 2 two step simplified finite rate chemistry model Also,the results between simulation and experiment were compared.

Key words: Supersonic combustion ramjet engine;Hydrocarbon fuel combustion;Supersonic combustion;Nu-merical simulation

摘要： 发展了二维超燃流场的数值模拟计算程序 ,用来进行高温富油燃气超燃流场的数值计算。数值解法采用了 Mac Cormack预估 -校正两步显式格式求解矢通分裂形式的 N- S方程组 ,湍流模型采用了壁面率修正的 Baldwin- Lomax代数方程模型和用于剪切混合层的普朗特混合长度模型。在超燃计算中 ,应用 C2 H4- O2 两步反应的有限速率化学反应模型 ,模拟高温富油燃气超燃试验的试验状态。计算结果表明 ,在高温富油燃气超燃流场中 ,热量释放较少

关键词: 超音速冲压喷气发动机;烃类燃料燃烧;超音速燃烧;数值模拟