先进双发民用飞机跨音速绕流数值模拟  

NUMERICAL SIMULATION OF TRANSONIC FLOW OVER AN ADVANCED TWIN ENGINE TRANSPORT AIRCRAFT

作　　者：鄂秦[1] 李杰[1] 李凤蔚[1] 刘积仑 于建中 

机构地区：[1]西北工业大学飞机工程系 [2]中国航空工业总公司民用飞机总体设计部

出　　处：《计算物理》1997年第4期493-495,共3页Chinese Journal of Computational Physics

基　　金：航空科学基金

摘　　要：采用求解椭圆型和抛物型偏微分方程的方法及多块网格技术，生成机翼／机身／短舱／挂架复杂组合体外形的贴体及与边界正交的计算网格。应用有限体积法高效求解欧拉方程，模拟先进双发民用飞机的跨音速绕流，并计入机翼边界层的粘性效应，获得存在短舱、挂架干扰的翼身组合体气动特性。计算表明，短舱、挂架对超临界机翼的气动特性有显著的影响。A body fitted orthogonal grid around complex configurations including wing, body, pylon and nacelle has been successfully generated by applying the multi block grid technique and the method of solving elliptic and parabolic partial differential equations. The transonic flowfield and aerodynamic characteristics of the advanced twin engine transport aircraft are also simulated numerically by using finite volume methods to solve the Euler equations with high efficiency, and the viscous effect of wing boundary layer is considered. Results of the calculation show that pylon and nacelle have significant effect on the supercritical wing aerodynamic characteristics. the numerical results are in good agreement with the experimental wing surface pressure distribution data.

关 键 词：翼身组合体 短舱 挂架 干扰 网格生成 跨音速流 

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]