高超声速再入钝头体表面热流计算

采用边界层外缘无黏流场数值求解三维可压缩定常Euler方程,将所得物面压力分布作为边界层外缘条件,用于边界层内跟踪流线的轴对称比拟工程算法,计算高超声速有攻角再入钝头体的表面热流。某钝双锥算例结果表明:算得的表面热流与实验数据吻合很好。该方法较纯工程算法提高了精度,较数值求解整个流场Navi-er-Stokes方程节省计算时间,对准确计算全轨道飞行复杂形状高超声速飞行器表面的热流分布有一定价值,适宜高超声速飞行器方案设计阶段气动热环境预测的需要。

Calculation of Aerodynamic Heating Distributions for Hypersonic Reentry Blunt-Nosed Bodies

An effective code for calculating the aerodynamic heating rates of hypersonic reentry blunt-nosed bodies at incidence based on the axisymmetric analogue which need track the inviscid surface streamlines was put forward in this paper.The boundary layer edge conditions were determined by using CFD method to solve Euler equations of three dimensions.The computation results of a bentnose biconic showed that the method was found to yield reasonably accurate laminar heating rates with experimental data,which coul...