带副翼的翼身组合体绕流的Euler方程解  

Euler Solution of a 3D Wing-Body Configuration with Aileron

作　　者：李津[1] 朱自强[2] 吴宗成[2] 陈泽民[2] 

机构地区：[1]北京航空航天大学理学院 [2]北京航空航天大学飞行器设计与应用力学系

出　　处：《北京航空航天大学学报》2000年第6期680-683,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：提出了一种求解带副翼偏转的翼身组合体绕流的Euler方程计算方法 .将对接分区网格与分区求解算法相结合 ,有效地求解了绕此外形的复杂流动 .提出了一种满足通量守恒的内边界耦合条件 .数值方法中选用VanLeer分裂格式离散无粘通量项 ,并构造了一种限制器 (Limiter)函数以保证TVD性质 .数值算例表明本文方法是求解带操纵面偏转的翼身组合体绕流的有效方法 .A Euler method for solving the flow around a wing body configuration with deflection of control surface (aileron) is presented. Using the combination of patched grid and domain decomposition techniques, the complex flow around this kind of configuration is effectively solved. An internal coupling condition is given to make the conservation of flux satisfied. In the computation Van Leers scheme is used to discretize the inviscid flux terms and a new Limiter function is constructed to realize TVD character. Numerical results show that present method is an effective one for solving the flow around wing body configuration with control surface deflection .

关 键 词：机翼空气动力学 绕流 偏转操纵面 EULER方程 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]