复杂前机身-进气道组合体的流场计算  

Solution of Euler Equations for Complex Forebody-Inlet Combinations

作　　者：郑小清[1] 沈慧俐[1] 纪名刚[1] 邢宗文 

机构地区：[1]西北工业大学,陕西西安710072

出　　处：《空气动力学学报》1992年第2期261-265,共5页Acta Aerodynamica Sinica

摘　　要：本文提出了一种能够对复杂前机身-进气道组合体进行流场计算与气动分析的方法。通过求解Euler方程来模拟前机身-进气道组合体在亚、跨、超声速,不同攻角和发动机流量条件下的各类流场。A new methodology on the simulation of aircraft fore-body-inlet combination flow fields has been developed. The solution algorithm is based on the Jameson-type finite volume, Runge-Kutta time stepping scheme. Efforts of this paper are made towards the application of block-structured grids. Three computational zones are used to model the. flow fields, this greatly relieves the restrictions on computer memory size and simplifies the mesh generation requirements. Flow solutions are executing on each zone in turn and coupled by determining the fluxes across the interface. A new enthalpy damping formula is constructed for the energy equation to accelerate convergence. The treatment method for inlet exit boundary, developed by the first author, is adopted, featuring no reflection to downwind waves, in which only flow mass is needed to be specified.The solution algorithm is applied to the calculation of integrated flow fields about a missle forebody-inlet configuration and a supersonic fighter inlet. The results achieved proved to be satisfactory. Highlighted in this paper are the steady states established for integrated flow fields of a supersonic fighter at angles of attack up to 30 degrees.

关 键 词：流场 进气道 欧拉方程 有限体积法 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]