A hypersonic pulse tunnel is designed in this paper, which has multiple running modes based on gun tunnel and shock tube theory.
本文设计了一座具有多种运行方式的高超声速大型脉冲风洞，该风洞可以采用炮风洞和激波管两种运行方式。
2
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.