Parametric Studies of Shock Wave/Boundary Layer Interactions over 2D CompressionCorners at Mach 6

摘要

Results fron a series of experiments performed in the VKI H-3 hypersonic windtunnel at Mach 6 with flat plate and flat plate/two dimensional (2D) compression ramp configurations simulating deflected control surfaces (rudders, elevons, flaps) of hypersonic vehicles are presented. The study falls within the framework of a more general investigation on shock wave/boundary layer interactions. The main experimental measurement technique was infrared thermography. The technique and data reduction models were improved in order to achieve state of the art accuracy levels. The model configurations considered have involved sharp and moderately blunt leading edges, as well as additional (periodic) leading edge disturbances. The thermal effect and the behavior of streamwise striations, detected in reattaching flow regions and interpreted as the footprint of Goertler vortices developing due to the concave flow curvature in such regions are discussed. Extensive comparisons of heat transfer data in regions of shock wave/boundary layer interaction, from the present work and other investigators, with simple theoretical predictions are presented. These led to the development of a new peak heating correlation, based on the reference temperature method, which was found to apply to two and three dimensional fully laminar, transitional and fully turbulent interactions, and to provide accurate engineering estimates of peak heating even in the presence of severe heat transfer non-uniformities (striations).