自由活塞激波风洞

自由活塞激波风洞是一种使用自由活塞压缩器驱动的高焓脉冲型激波风洞。这种风洞是由R J Stalker提出并在澳大利亚国立大学首先建成和逐渐发展起来的高焓实验设备。经过30多年的改进与发展,日趋完善,现已成为研究高超声速气动加热、计及真实气体效应的气体动力学现象、特别是超声速或高超声速燃氢冲压发动机(scamjet)的重要设备之一,受到国际上航空航天界的重视。本文概述了自由活塞激波风洞的发展过程,系统地阐述了这种设备的结构特点和运行原理,给出了性能参数的计算方法和算例,及其性能指标,并讨论了这类风洞的优缺点。

A FREE-PISTON SHOCK TUNNEL

One of the high-enthalpy intermittent wind tunnels is the free-pistonshock tunnel, where a free heavy piston compressor is used. It is first suggested and built by Prof. R. J.Stalker at the Australian National University, Canberra, Australia. The free-piston shock tunnel is unique in its ability to provide very-high-temperature, high-pressure test conditions, and can be used to produce test section flows with stagnation enthalpies greater than those corresponding to earth satellite velocity, so this type of facility has enabled experimental study of a range of real gas effects in high-speed hypersonic aerodynamics. Especially, the high enthalpy, high density capabilities of the free-piston shock tunnel can be effectively used in the research of the new propulsion-scramjet as well. More recently, the free-piston shock tunnels have been attached great importance in the field of the aeronautical engineering and space technology internationally.A summary of the free-piston shock tunnels is made in this paper with a systematic exposition of their developments, constructional characteristics, operating principles, calculating methods of the performance parameters.