Abstract
Pressure- and temperature-sensitive paint measurements can make possible the measurement of global surface pressure and temperature distributions on a body at a time, which are different from point measurement by conventional sensors. Shock tunnels have been widely used to make hypersonic flows at low cost and to examine the flowfield around high-speed vehicles. However, they have a limitation of duration. The present study applies pressure- and temperature-sensitive paints to investigate an interaction flowfield due to two bodies, i.e., a hemisphere-cylinder and a delta wing, in a hypersonic flow with M∞=8.1. As a result, the present methods were found to be useful and effective to analyze the flowfield.
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