This paper presents experimental results of flap heat transfer and pressure characteristics on a blunt cone in shock tunnel.
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。
In this paper, basic composition, design methods, and debugging situation of a supersonic MHD technical experimental system based on shock tunnel 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。
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 shock tunnel.
本文综合飞行数据和激波风洞中的实验结果，给出了一个计算湍流底部热的工程方法。
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