载人飞船返回舱的气动热流率分布

高超声速有攻角钝头轴对称体的载人飞船返回舱的热流率计算，目前已有很多方法。迎面球冠的对流加热率可由风洞试验结果和Ｌｅｅｓ及Ｄｅｔｒａ－Ｋｅｍｐ－Ｒｉｄｄｅｄ等的驻点热流理论作较好预测。拐角圆环区是返回舱上加速流最剧和气动加热最严重的地方。试验结果表明迎风倒锥附着流表面的热流率和背风倒锥分离流表面的热流率分别比零攻角驻点的热流率的１５％和５％还低。

THE AERODYNAMIC HEATING DISTRIBUTIONS OF CAPSULE TYPE RE-ENTRY VEHICLE

This paper introduces the aerodynamic heating distributions of capsule type re-entry vehicles.Many methods have beed developed for calculating heat-transfer rates on blunt-nosed axisymmetric bodies at angle of attack in hypersonic flows.Convective heating rates on the spherical segment entry face can be predicted by the use of wind tunnel results and stagnation-point theories of Lees and Detra-Kemp-Ridded.Toroid is a region of rapidly accelerating flow and experiences severe aerodynamic heating.Heat-transfer rates measured in the windward attached and lee-side seperated regions of conical section indicated that these heating rates were less than 15% and 5% of the stagnation-point heat-transfer rates respectively.