Experimental Studies of Shock Wave Boundary Layer Interaction on Suction Side of Fan Representative Profile

Transonic compressors encounter significant challenges from shock formations due to high-speed supersonic blade tips, particularly at high altitudes where lower Reynolds numbers result in laminar-boundary layer separation and increased mixing losses. Understanding shock wave boundary layer interaction (SBLI) is essential for improving compressor performance. This study examines SBLI under varying Reynolds numbers, simulating higher altitude conditions in a transonic blow-down wind tunnel. Using an inlet valve setup at IMP-PAN to control inflow total pressure and Reynolds numbers, the study also reveals an increase in turbulence. Findings indicate that laminar-to-turbulent transition occurs upstream of the shock wave, resulting in interaction with a turbulent boundary layer, even at lower Reynolds numbers.