面向飞行器概念设计的全速域气动分析工具

An aerodynamic analysis tool for aircraft conceptual design at full speed range

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 fo r a rb itra ry Mach number f low was developed in this paper. This tool consists of three methods fo r three individual Machnumber ranges： 1） A f inite volume fu l l potential method on adaptive Cartesian grids fo r subsonic and transonic flow ; 2） A f in ite volume Euler method on adaptive Cartesian grids fo r supersonic flow ; 3） An empirical panel method based on local surface inclination methods fo r hypersonic flow . The feasibility and accuracy of the proposed method are validated by several typical cases of different flows around ONERA M 6 win g , D LR -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 w ith fu l ly automatic grid tre a tm e n t, and the results confirm the capacity of the present method in applications fo r unconventiodesign in a wide range of Mach numbers.