翼吊式双发民机机体/动力装置一体化数值分析

NUMERICAL SIMULATION OF TRANSONIC FLOW OVER WING-MOUNTED TWIN-ENGINE TRANSPORT AIRCRAFT

介绍了多块网格技术与流场分区求解方法在翼吊式双发民机机体／动力装置一体化研究中的应用．数值求解Ｅｕｌｅｒ方程模拟复杂组合体绕流．采用边界展方程／Ｅｕｌｅｒ方程耦合迭代技术进行器面粘性修正．为保持Ｅｕｌｅｒ方程求解中计算网格固定，粘流／无粘流耦合迭代采用表面源模型．该方法对某民用飞机模型跨音速绕流流场进行了数值模拟，机翼表面计算压力分布与实验吻合良好．

A numerical method has been developed for analyzing the flow around advanced transport aircraft with wing-mounted nacelles. The method is based on a multi-block pointmatched grid generation approach coupled with zonal solving strategy for complex flow field. In this method, the flow field is divided into a number of non-overlapped blocks by a cut-out technique. H--types grids are generated independently in each block using an elliptic grid generation method, in which the control of the grid quality is accomplished by the forcing function technique of Hilgenstock. An explicit 3-stage Runge-Kutta algorithm based on Jameson's finite volume scheme for the Euler equations has been developed that is applicable to the multi-region H-type grids. The present method has been applied to a complex transport aircraft configuration consisting of lowwing/fuselage combination with wing-mounted pylon/nacelles. On the wing surfaces, the viscous boundary layer effects is accurately added with the employment of the viscous-inviscid interaction technique nsing a surface transpiration approach by two dimensional strip theory. Computational results and comparisons with experiment are presented. The good agreement indicates that the present method is effective and robust in prediction the flow field around complex transport aircraft configurations.