面向飞行器概念设计的全速域气动分析工具

摘要

为满足飞行器概念设计中快速气动计算的需求,研究和开发了一种全自动化全速域气动分析集成工具.针对不同的速度域,该工具由三种计算方法组成:1)亚、跨声速情况,采用基于自适应直角网格的非线性全速势方程有限体积解法;2)超声速情况,采用基于自适应直角网格的欧拉方程有限体积解法;3)高超声速情况,采用基于当地表面斜度法的面元法.不同速度域的多种构型飞行器的算例结果表明,该集成工具的计算精度满足要求,且自动化程度高、收敛速度快,可应用于飞行器概念设计的快速气动分析.%For fast and automatic aerodynamic computation in unconventional aircraft conceptual design,a full-automatic aerodynamic analysis tool for arbitrary Mach number flow was developed in this paper.This tool consists of three methods for three individual Mach number ranges:1)A finite volume full potential method on adaptive Cartesian grids for subsonic and transonic flow;2)A finite volume Euler method on adaptive Cartesian grids for supersonic flow;3)An empirical panel method based on local surface inclination methods for hypersonic flow.The feasibility and accuracy of the proposed method are validated by several typical cases of different flows around ONERA M6 wing,DLR-F4 wing-body,unmanned aerial vehicle (UAV) with a blended wing body (BWB),HL-20 lifting-body,and AS-202 capsule.The validation cases demonstrate a fast computation convergence with fully automatic grid treatment,and the results confirm the capacity of the present method in applications for unconventional aircraft conceptual design in a wide range of Mach numbers.