This paper presents experimental results of flap heat transfer and pressure characteristics on a blunt cone in shocktunnel.
本文介绍了一种在激波风洞中取得的，装在钝锥模型上的控制翼热流及压力特性实验结果。
2
In this paper, basic composition, design methods, and debugging situation of a supersonic MHD technical experimental system based on shocktunnel are introduced.
基于此，介绍了基于激波风洞的超声速磁流体动力技术实验系统的基本组成、设计思想和调试情况。
3
An engineering formula for estimating turbulent base heat transfer of hypersonic flow is given on the basis of flight data and the experimental results in shocktunnel.