The main objective of the present study is to subject NALPSP-02, an indigenously developed binary pressure sensitive paint, to supersonic flow conditions. An experimental study was carried out on a double-delta wing model at a free stream Mach number of 2.0 in the 0.3 m trisonic wind tunnel at NAL. Pressure Sensitive Paint (PSP) technique was used to measure the pressure distribution on the lee side of the double delta wing at an incidences of 0°, 5°, 10° and 15°. The PSP results were compared against surface pressure data obtained using conventional pressure taps on the same model.