三维高超声速喷流干扰流场的数值模拟  

3D NUMERICAL SIMULATION OF HYPERSONIC JET INTERACTION FLOWFIELD

作　　者：李桦[1] 王承尧[1] 

机构地区：[1]国防科技大学航天技术系

出　　处：《推进技术》1999年第2期53-55,共3页Journal of Propulsion Technology

摘　　要：采用ＬＵ隐式方法求解了有限体积法离散的完全Ｎ－Ｓ方程，数值模拟了三维高超声速喷流干扰流场。计算中采用了Ｊａｍｅｓｏｎ的当地极值递减（ＬＥＤ）格式和Ｂａｌｄｗｉｎ－Ｌｏｍａｘ代数湍流模型，与实验结果相比较，数值方法对附体流动计算较准确，对分离区附近流场计算有一定误差。A time dependent, implicit,finite volume,lower upper(LU) numerical method was developed to solve the three dimensional Navier Stokes equation. The numerical procedure uses Roe's flux difference splitting and Jameson's LED scheme for the connective terms and central difference scheme for viscous terms. Baldwin Lomax algebraic turbulence model was used to enclose the governing equations. Numerical solutions of hypersonic jet interaction flowfield with attack angle are obtained, and the numerical results were compared with experimental data.

关 键 词：三维流 高超音速流 喷流干扰 数值仿真 N-S方程 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] V231.3