Pressure sensitive paint measurements on a delta-wing in supersonic flow

Experiments have been performed documenting the pressure field on the lee-side of a delta-wing at three incidence angles (5 degrees, 10 degrees, and 15 degrees) and at Mach 1.8 using a PSP (Pressure Sensitive Paint) technique. The delta-wing model having a leading edge sweep of 60 degrees was instrumented with 31 spanwise pressure ports at 68% of mean chord location. The Optrod-B1 binary paint was utilised and the PSP images were processed employing a resection based methodology. The comparisons of PSP results with those measured employing pressure taps show good agreement at different incidence angles.