A Study on Characteristics of Shock Train inside a Shock Tube

来源 :第14届亚洲显示会议(The 14th Asian Symposium on Visualization) | 被引量 : 0次 | 上传用户:yd476789385
下载到本地 , 更方便阅读
声明 : 本文档内容版权归属内容提供方 , 如果您对本文有版权争议 , 可与客服联系进行内容授权或下架
论文部分内容阅读
  Shock tubes are devices which are used in the investigation of high speed and high temperature flow of compressible gas.Inside a shock tube,the interaction between the reflected shock wave and boundary layer leads to a complex flow phenomenon.
其他文献
The cylindrical converging shock reflection over a curved wedge is investigated experimentally in a converging shock tube.
In hypervelocity flows the speed of the considered fluid is much larger than the speed of sound.
The present study describes the application of Particle Image Velocimetry(PIV)to investigate the compressible flows in the sonic and supersonic jet flows.
The technology of oil visualization is be used to depict the local separation flowfield structures induced by 3D wedge which simulate flap in hypersonic wind tunnel.
The reaction control systems(RCS)will be the main and key technology to implement the highmaneuver,fast response,and high-accuracy for hypersonic flight vehicle,has been widely used in many hypersonic
Due to the high speed of the supersonic flow in the scramjet combustor,the residence time of fuel remains only a few milliseconds.
A computational scheme of fluidic was conducted which utilizes coflowing and countercurrent shear layers to control thrust vector in the absence of moving parts.
In the development of hypersonic vehicles,a spiked-nose may promote the reduction of shockinduced drag and the decrease of heat flux over blunt bodies.
At supercritical conditions a porous strip(or slot strip)placed beneath a shock wave can reduce the drag by a weaker lambda shock system,and increase the buffet boundary,even may increase the lift.
In this paper,flow and acoustic measurements results of an experimental investigation of supersonic jets exhausting from 30° and 60° beveled nozzles will be presented and discussed.