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 and 0.83. The convex-corner angle and swept angle were, respectively, 10-17 degrees and 5-15 degrees. Expansion and compression near the corner apex were clearly visualized. For the test case of shock-induced boundary layer separation, there were greater spanwise pressure gradient and curved shocks. The acquired PSP data agree with the experimental data measured using the Kulite pressure transducers for a subsonic expansion flow. For a transonic expansion flow, the discrepancy was significant. The assumption of a constant recovery factor is not valid in the separation region, and temperature correction for PSP measurements is required.

Automated summary

This study used pressure-sensitive paint (PSP) to determine the surface pressure distributions for a compressible swept convex-corner flow. It found greater spanwise pressure gradient and curved shocks in the case of shock-induced boundary layer separation. The PSP data agreed with experimental data for subsonic expansion flow but showed significant discrepancy for transonic expansion flow, requiring temperature correction.