基于轴对称比拟的高超声速复杂外形气动热预测方法研究

摘要

Axisymmetric analogue is an effective method for predicting aerodynamic heating on hypersonic vehicles.In order to overcome the disadvantages of the original method ,a three-dimensional linear de-scription of surface and flowfield is proposed in Cartesian coordinate system and equations for computing streamline metric coefficients are derived correspondingly .Calculation of heating rates in stagnation region is expanded ,downstream of which a new marching scheme introduced .Based on improved axisymmetric analogue ,an engineering code has been successfully developed to compute the approximate heat flux of general three-dimensional hypersonic vehicles at angles of attack for perfect gas .A spherically blunted cone and double ellipsoid are investigated to verify the robustness and test the efficiency of the code ,fi-nally satisfactory agreement with wind tunnel experimental results is found .%轴对称比拟法是高超声速飞行器气动热计算的一种有效方法。针对轴对称比拟法应用时公式推导繁琐、变量迭代复杂、计算量大的缺陷，直接在笛卡尔坐标系下采用三维线性方程拟合物面方程及流场变量，推导出相应的流线尺度因子计算公式，扩展了驻点区热流密度的计算方法，提出了一种驻点区下游流线推进格式。以改进的轴对称比拟法为基础，将边界层外无粘流场数值方法与边界层内气动热工程算法进行耦合，发展了一套适用于三维复杂外形飞行器的气动热计算方法。通过对球头钝锥和双椭球算例进行验证，结果表明：方法计算效率较高，适用范围较广，热流计算结果和实验数据吻合良好。