In this paper the results of calculations of the coefficients of skin friction and heattransfer (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。
2
An engineering formula for estimating turbulent base heattransfer of hypersonic flow is given on the basis of flight data and the experimental results in shock tunnel.