摘要
该文针对飞行器设计中的机体和进气道的一体化问题,采用分区结构搭接网格技术,对机体外流场采用有限体积法求解Eu ler方程,进气道内流场采用有限体积法求解N-S方程,发展了求解三维超音速前机身/进气道内外流的Eu ler/N-S方程分区处理程序,同时对某型飞机的前机身/进气道流场进行了一体化模拟。通过分析计算出的附加阻力和畸变系数等结果的合理性验证了计算程序的正确性。同时通过对计算域采用不同的密度网格进行计算,分析研究了网格疏密对计算结果的影响。
A simulation method is developed for analysing the flow field of some components in a kind of aircrafts, which include the inlet and the forebody. In the simulation, the zonal structured grid technique and the patched grid technique are applied. The Finite Element Method is used to solve the Euler/N - S equations. The correctness of the method is proved through analyzing the calculated results of the additional resistance and the distortion factor. Meantime, the influence of the density of grids on the precision of the calculation is studied through increasing the density of grids in the computation.
出处
《计算机仿真》
CSCD
2006年第11期47-49,90,共4页
Computer Simulation
关键词
分区网格
进气道
数值计算
附加阻力
畸变系数
Zonal grid structured technique
Air inlet
Numerical calculation
Additional resistance
Distortion factor
