机翼机身跨声速绕流的计算

Transonic Flow Simulation for Wing-Body Configurations

本文采用变换与数值网格生成方法，对由椭圆抛物面描述的每一个展向曲面进行网格生成，引人一种用于控制网格疏密分布的函数变换方法，其特点是易于对不同族网格线分别控制，根据物面梯度自适应地调整网格的疏密。用有限体积法计算守恒型全速势方程跨声速绕流，对Ｍ－１００翼身组合体进行计算。理论计算结果与实验结果表明，本文方法有效。

A mapping/numerical grid generation method and an efficienttransonic flolw calculation algorithm have been developed for the analysisof general wing-body configurations. Every spanwise grid surface is de-scribed by an elliptic paraboloid. The mesh is generated by a conformalmapping procedure and a nearly orthogonaI numerical scheme. Grid dis-tributions are effectively controlled through the using of a stretchingfunction mapping method. The scheme is general and efficient,andgenerates nearly orthogonal grid systems in the field. The flow analysisalgorithm uses a finite volume approach to solve the full potential equation in conservation form. Computed resuIts for a M-100 configurationsshow a good agreement with test data.