Shock-Wave/Boundary-Layer Interaction Studies

Downstream St Contour X Y LaminarHeat transfer rates on a cone-flare model.

Hypersonic Shock-Wave/Boundary-Layer interactions are some of the most complex phenomena in compressible aerodynamics, with applications to scramjets and external vehicle aerodynamics. Extensive studies of shock-wave/boundary-layer interactions on axis-symmetric cone/flare models have been carried out by the Notre Dame Hyper Lab, utilizing advanced diagnostic technologies such as infrared thermography and pressure-sensitive paint. The use of unsteady pressure sensitive paint uniquely allows for the global time-resolved structure of these interactions to be investigated and new scaling laws to be proposed.