Application of PSP on the SWiFT Model in the National Transonic Facility
This report details the results from a Pressure Sensitive Paint test on a blended/hybrid wing body model conducted at the National Transonic Facility. This test investigated potential instabilities that can occur at high Reynolds number and low Mach number testing conditions. The upper surface of the model was coated with pressure sensitive paint, and data was collected at various Mach numbers and angles of attack. For this test, typical pitch-pause testing was completed as well as a novel continuous sweep functionality that provided much greater angle of attack resolution. Results from this test will be presented, including indications of potential instability points in the testing envelope.
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