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
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.
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 boundar
Open-loop active control of bursting process and drag reduction in wall turbulence is realized by utilizing synchronous and asynchronous vibration of double piezoelectric vibrators placed along the sp