Experiments on Hypersonic Laminar-Turbulent Transition Control Using Passive Porous Coatings

摘要

The laminar-turbulent transitions of the hypersonic boundary layer is studied experimentally on the blunt cone with the porous coating at free stream Mach number M=8, to determine the effect of the ultrasonic-absorbing coating on the transition location at zero angle of attack. It is shown that, for the cones with small nose bluntness which increases the laminar run, the passive porous coating gives an additional sufficient delay in transition.