Visualization of Suppressed Shock Wave/Turbulent Boundary Layer Interaction Using Cryogenic Wall Cooling
Yuma Miki, Leo Ando, Maria Acuna, Kiyoshi Kinefuchi

TL;DR
This study investigates how cryogenic wall cooling with liquid nitrogen affects shock wave/turbulent boundary layer interactions in supersonic flow, showing that cooling suppresses boundary layer separation and alters flow structures.
Contribution
It provides experimental evidence on the effects of cryogenic wall cooling on SWTBLI, demonstrating suppression of separation and consistency with classical interaction theory.
Findings
Cooling reduces interaction length by approximately 40-30%.
Boundary layer separation is suppressed under cryogenic cooling.
Flow structures align with classical Chaman's free interaction theory.
Abstract
To investigate the wall-cooling effects on shock wave turbulent/boundary layer interaction (SWTBLI) with limited experimental data, a supersonic wind tunnel wall was cooled using liquid nitrogen as the cryogenic coolant. Under the condition of the mainstream Mach number, in the range of 2.02-2.04, the wall temperature was cooled to 88-92 K, corresponding to a wall-to-recovery temperature ratio of 0.31-0.33. The flow structures with and without wall cooling were observed using the schlieren method. The reflected shock motion or interaction length in the schlieren image suggested that boundary layer separation was suppressed under the cooling condition in relation to that under the non-cooling condition, and the suppressed ratio of the cooling-to-uncooling interaction length was approximately 0.60-0.72. Additionally, while the mainstream state and wall temperature near the separation were…
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