高超声速飞行器翼面气动加热的工程计算方法

Engineering Calculation of Aerodynamic Heating for Airfoils of Hypersonic Vehicles

翼面气动加热是高超声速飞行器面临的核心问题之一。文中基于参考焓法及经验公式,采用片条理论对飞行器翼面进行热流密度估算;考虑了不同飞行参数及翼型参数对翼面迎风面表面温度分布的影响;给出了高超声速飞行器翼面气动加热工程计算流程。采用文中方法,对高超声速飞行器常用的双凸形翼型进行气动加热计算,结果表明攻角、飞行马赫数、前缘后掠角、翼型相对厚度对翼面温度分布影响显著。该方法可用于高超声速飞行器翼面快速设计。

The aerodynamic heating of airfoils is one of main problems of hypersonic flight vehicles.In this paper,firstly,based on the reference enthalpy method and the empirical formula,the aerodynamic heating flux of hypersonic flight vehicles was studied using the strip theory.Secondly,for both of the boosted period and the cruise period,the temperature distribution was calculated under different angles of the attack and airfoils.Furthermore,based on above steps of solutions,a solution flow chart of the aerodynamic heating of airfoils of hypersonic flight vehicles was given.Considering an example about a biconvex airfoil,its aerodynamic heating was calculated by the method in this paper.The results indicate that the angle of the attack,the sweepback angle of wing leading edge and the relative thickness of the airfoil significantly influence on the temperature distribution of airfoils.This method is helpful for preliminary design of hypersonic flight vehicles.