跨声速翼-身组合体三维粘性流场的数值模拟  

Numerical Simulation of Three-Dimensional Viscous Transonic Flowfield of A Fined-Body Configuration

作　　者：乐贵高[1] 吴萍[1] 潘书山 

机构地区：[1]南京理工大学,江苏南京210094

出　　处：《弹箭与制导学报》2003年第S5期184-186,197,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：建立非结构网格系统下求解飞机外挂物三维翼身组合体绕流的 N-S 方程组的数值方法,湍流模型为Spalart-Allmaras 方程模型。数值方法包括三阶 MUSCL 型 TVD 格式离散无粘通量项和中心差分离散粘性通量项。数值模拟了雷诺数为 Re=7.8×10~6,马赫数分别为0.6、0.95和1.2流动问题,与风洞实验数据吻合很好,表明该方法是求解三维翼身组合体流场的有效方法。A numerical method for solving the Navier-Stokes equations of the three-dimensional fined-body configurations flow interference of the fighter plane carriage in the unstructured grid system is founded.The turbulence model is Spalart-Allmaras equation model.In this method,the MUSCL typical TVD scheme with the third order accuracy is employed to discrete the inviscid flux and the central difference is employed to discrete the viscous flux.The flow cases including Reynolds'Re=7.8×10~6,the Mach number of 0.6,0.95 and 1.2 are simulated numerically.The results agree well with the data in wind tunnel experiment,which show the present method can be solved the three-dimensional fined-body configuration flow efficiently.

关 键 词：翼-身组合体 跨声速流 N-S 方程 非结构网格 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]