不对称喷管欠膨胀超声速射流的数值模拟  

Numerical simulation of supersonic jets of asymmetric nozzles

作　　者：乐贵高[1] 马大为[1] 马艳琴[1] 李志刚[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《流体力学实验与测量》2003年第4期17-21,共5页Experiments and Measurements in Fluid Mechanics

摘　　要：采用改进的MUSCL格式解三维可压缩平均雷诺纳维尔 斯托克斯方程组,湍流模型为Spalart Allmaras代数模型,数值模拟了四种调整片不对称喷管在喷口压比为2.0、2.8、3.4和4.0条件下的欠膨胀超声速射流场,获得了射流场流谱和参数分布,并给出了单调整片不对称喷管出口压强比与射流偏转角和扩张角的分布曲线,计算结果和实验数据符合良好。The three-dimensional compressible,Reynolds-averaged Navier-Stokes equations with Spalart-Allmaras algebraic turbulence model are solved by using the modified MUSCL scheme.The underexpanded jets from tabbed nozzle under four kinds of nozzle pressure ratios of 2.0,2.8,3.4 and 4.0 are simulated numerically.The jet flowfield pictures and flow parameter distributions are obtained.The distribution curves of nozzle pressure ratios influencing on the jet deflection angle and divergence angle for 1-tab nozzle are given as well.The numerical results agree with experimental data well.

关 键 词：飞行器 数值模拟 欠膨胀超声速射流 纳维尔-斯托克斯方程 不对称喷管 推力向量控制系统 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]