Investigation of Heat Transfer to a Flat Plate in a Shock Tube.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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The heat transfer mechanisms taking place in the flow induced behind a shock wave travelling across a flat plate were investigated for flat plates with sharp and rounded leading edges. The boundary layer behind the shock is described by a transient boundary layer followed by a steady state boundary layer as the effects of the leading edge are transmitted downstream. The use of a multichannel high speed transient data recorder allowed thin film heat transfer gages at up to eight axial locations along the length of the flat plate to be simultaneously sampled. Heat transfer rate histories for each axial location were time correlated to the same flow conditions. The results indicate the existence of a threshold free system velocity relative to the plate above which are confined to some narrow interval. For Mach numbers below 1.22, the sharp leading edge flat plate experienced heat transfer rates in excess of theory, but the rounded leading edge flat plate data showed a consistent correlation between heat transfer magnitude and axial location on the plate with limited data, the rounded plate showed no such correlation.