Abstract
Using thin-film resistance technology characterized by a fast response time and a high sensitivity to heat transfer, a method is developed to measure mean Stanton number in a supersonic blowdown facility under near-adiabatic conditions. The successful application of thin-film gauges required corrections for the changes in total temperature with time and for departures from one-dimensional heat conduction in the gauge itself. This method was then demonstrated in a shock wave-turbulent boundary layer interaction generated by a 16° compression corner in a Mach 2.84 flow. The results show a strong increase in Reynolds analogy factor across the shock, and it appears to level off at a value of 2.15, which is approximately 1.75 times the usually quoted value for an unperturbed boundary layer flow.
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