Affiliations: National Research Council, Institute for Aerospace
Research, Montreal Road, Ottawa, K1A0R6, Canada. | Office National d'Etudes et de Recherches
Aérospatiales, Département d'Aérodynamique Fondamentale et
Expérimentale, 8 Rue des Vertugadins, 92190 Meudon, France.
Abstract: A comparative wind tunnel test of various Pressure Sensitive Paint
(PSP) formulations has been performed at the Institute for Aerospace Research
(IAR) 1.5 m × 1.5 m Trisonic Blowdown Wind Tunnel. The model under study
is a prototype supercritical wing of a half model. The results are presented at
the cruise Mach number: M = 0.74. The effect of the Reynolds number on the
pressure distribution is assessed by varying the stagnation pressure of the
flow. The evaluated paints all use the same porphyrin molecule as the
luminescent sensor and the differences in sensitivity to pressure and
temperature are a result of the PSP binder, which differs for each formulation.
Examples of the processed results are given and the accuracy of the different
PSP formulations is also discussed.