In this paper the results of calculations of the coefficients of skin friction and heat transfer ( Stanton number) on the surface of hypersonic flight vehicle are presented. 本文给出了高超声速飞行器表面摩阻和传热系数(斯坦顿数)的计算结果。
The Stanton Number for each cross section of converging-diverging tube is investigated by adapting the dimensionless temperature distribution normal to the wall of the tube, and the prediction formulae for heat transfer are obtained. 通过引入无因次温度分布式,求解缩放管内任一截面的传热斯坦顿数,并以此为基础导出了缩放管整体传热准数预测公式。