高超声速气动热环境工程算法

Engineering Algorithm for Aeroheating Environment of Hypersonic Aircrafts

对高超声速飞行器气动热环境工程算法进行研究。基于Prandtl边界层理论,将流场分为边界层外的无粘流场和边界层内粘性主导的区域,并将两者的工程算法相结合,发展了一套高超声速气动热的计算方法。对于无粘流区,边界层外缘参数的计算采用完全气体模型和平衡气体模型,利用等熵条件来确定;在边界层内部,基于参考焓方法,采用经典热流密度公式,确定物体表面的气动加热。采用此方法对一些简单三维外形进行了气动热计算,证明所述方法具有较高的精度。

The aeroheating environment engineering algorithm for hypersonic aircrafts is present.Basing on the Prandtl boundary layer theory,the whole flow field is divided into inviscid flow field out of the boundary layer and the viscosity-dominated inner boundary layer.Combining engineering algorithms for the two fields,an algorithm for hypersonic aerodynamic heating environment is developed.For inviscid flow,the parameters at the edge of the boundary layer are calculated by using constant entropy conditions for ideal and equilibrium gas.Within the boundary layer,based on the reference enthalpy method,the classical heat flux formula are used to determine the surface aerodynamic heating.Using this method,the heating rates for some simple three-dimensional shapes of aircrafts are calculated.The results show the high accuracy of the presented method.