Measurements of Reynolds analogy for a hypersonic turbulent boundary layer on a nonadiabatic flat plate.

The purpose of the described experiment was to obtain simultaneous measurements of skin friction and heat transfer at hypersonic Mach numbers, especially with conditions of considerable heat transfer. The experiment was conducted in air in the Ames Hypersonic Wind Tunnel, in which cold air was passed through an alumina storage heater system and heated to total temperatures ranging from about 670 to 1170 K. The nozzle was contoured to produce a flow at Mach 7.4. Thin-skin heat-transfer gauges were placed at equal intervals along the centerline of a sharp-edge flat plate, which was used as the model. A skin-friction balance and a boundary-layer pitot-pressure rake were mounted on each side of the centerline at a certain distance from the leading edge.