Abstract
This study presents the surface pressure and temperature measurements in a Mach 1.8 submillimeter supersonic wind tunnel with pressure-sensitive paint (PSP) and temperature-sensitive paint (TSP) techniques using PtTFPP and EuTTA as the pressure and temperature probes, respectively. The surface temperature profile was acquired by TSP and the temperature drop from the nozzle inlet to the test section was about 3.63 oC. The moderate temperature decrease measured by TSP was attributed to the paint embedded in the viscous layer and attached to the plastic plate as boned to the submillimeter wind tunnel. The estimate of the maximum error in the PSP data due to the temperature dependence is around 4.1 %.