多翼空空导弹复杂流场气动力计算  

Aerodynamic Force Computations of Complex Flow-fields around Multi-Wing Air-Air Missiles

作　　者：郑秋亚[1,2] 杨尊袍[3] 刘国俊[4] 

机构地区：[1]西安电子科技大学理学院,陕西西安710071 [2]长安大学理学院,陕西西安710064 [3]空军工程大学理学院,陕西西安710051 [4]中国航空计算技术研究所,陕西西安710068

出　　处：《空军工程大学学报（自然科学版）》2009年第4期1-5,共5页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：航空科学基金资助项目(01A31002)

摘　　要：为了高精度地确定导弹的气动力参数,为导弹合理的气动布局提供理论依据,对绕某外形多翼空-空导弹全弹体三维绕流流场进行了雷诺平均Navier-Stokes方程数值模拟,为了使方程封闭采用了Spalart-Allmaras一方程湍流模型,计算方法为Jameson的有限体积多步Runge-Kutta时间推进法和空间中心差分耦合人工粘性项,使用分区技术,通过求解椭圆型偏微分方程方法生成了连续拼接式多块结构化网格,在超音速带有攻角和有滚转角或无滚转角的条件下,获得了导弹弹体、舵翼和副翼上的气动力和力矩,计算结果与实验数据以及其它程序的计算结果吻合较好。结果表明:文中算法可用于真实复杂外形导弹、复杂流态下的气动力计算。To obtain the aerodynamic forces accurately and provide theoretic guide for the design of missile＇s configurations, a numerical simulation of the flow fields around an actual configuration of air - to - air missiles （AAM） is performed by solving the Reynolds averaged Navier - Stokes equations （RANS）. The Spalart - Allmaras （ S - A） one equation turbulence model is coupled to close the governing equations. The Jameson＇s finite volume multistage Rung - Kutta time - stepping scheme and spatial central difference coupled with artificial viscous terms are used in the computation. A patched multi -block structured grid is generated around the complex configuration using the multi -zone technique and elliptic partial differential equations. The simulations are conducted in supersonic flow at different angles of attack. Aerodynamic forces and moments acting on the body, rudders and ailerons of the AAM with or without angle of roll are calculated. These results agree well with the experiment and those using other codes, and they show that the scheme can be adopted in the computations of the complex flow fields around actual configuration of multi - wing missiles.

关 键 词：雷诺平均Navier—Stokes方程 湍流模型 有限体积方法 

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]