Global Visualization of Compressible Swept Convex-Corner Flow Using Pressure-Sensitive Paint

This study used pressure-sensitive paint (PSP) and determined the surface pressure distributions for a compressible swept convex-corner flow. The freestream Mach numbers were 0.64 0.83. angle were, respectively, 10–17° 5–15°. Expansion compression near corner apex clearly visualized. For test case of shock-induced boundary layer separation, there greater spanwise gradient curved shocks. acquired PSP data agree with experimental measured using Kulite transducers subsonic expansion transonic flow, discrepancy was significant. assumption constant recovery factor is not valid in separation region, temperature correction measurements required.