Abstract
Anodized aluminum pressure sensitive (AAPSP) and temperature sensitive paints (AATSP) were applied to a 30° compression corner model in the Mach 7.1 Hypersonic and High Enthalpy Wind Tunnel at the University of Tokyo, Kashiwa Campus. The measurement technique was able to capture spatially resolved unsteady hypersonic flow phenomena over the surface of the model at a rate of 10 Hz for pressure measurements and 30Hz for temperature measurements. High heating due to oblique shocks and flow stagnation was observed at the leading edge of the model. Shock-shock interactions, confirmed by schlieren imagery were clearly visible in the pressure distribution. Görtler vortices consistent with boundary layer growth over a concave wall were also visible in both the pressure and temperature maps produced by the AAPSP and AATSP. The tests demonstrate the effective use of AAPSP and TSP for spatially resolved measurements in hypersonic flow. The temporal resolution of the measurement was limited by camera technology, and can be improved without modifications to the luminescent sensors.
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