Experimental investigation and numerical analysis of hypersonic compression ramp heat transfer

For blunt-nosed, ramped flat plates at angles of attack of 0 degrees, 20 degrees, 30 degrees and 35 degrees, the heat transfer and the flow field around the compression ramp have been investigated experimentally based on infrared thermography measurement and Schlieren photograph observation in the NAL 1.27m and ONERA S4MA hypersonic wind tunnel at M-infinity =10.0 and Re-infinity=1.5 - 2.3 x 10(6)/m. We also compared CFD simulations using NAL and ONERA N. S, codes for the examination and comparison of the flow field and the magnitude of the heat transfer. The results showed an increase in heat transfer on the flat plate that was upstream from the corner and the reduction of heat transfer on the ramp when the leading-edge is blunt. An analytical study to obtain a single correlation for the measured heat transfer along the plates showed that ratio x/v(n) of x distance from the leading-edge and the nose radius is a dominant similarity parameter for heat transfer distribution on the ramp downstream of the reattachment as well as on the flat plate part upstream from the ramp corner.