PSP Measurements on a Delta Wing-Body Model in the NAL 1.2m Trisonic Wind Tunnel

This report presents results obtained during the commissioning tests of a PSP system based on DLR technology in the NAL 1.2m trisonic wind tunnel. Measurements were made on a delta-wing-body model using two different binary paints (Optrod-B1 and NAL-G type) at a freestream Mach number of 0.8 and a=10°. A typical PSP image integration time was about 11s during a tunnel blowdown duration of about 20s. The drop in total temperature was typically about 8°C during the image integration. The results showed small changes on surface pressures (between different blowdowns) arising from a drop in tunnel total temperature during a blowdown which may be expected from the paint properties. The surface pressure distributions obtained from the two paints showed high degree of consistency.