Cryogenic wall cooling at 95 K shifts the separation point downstream in Mach 2 shock-turbulent boundary layer interactions and reduces local heat flux, enabled by cryogenic temperature-sensitive paint measurements.
Investigation of Separation and Associated Heat Transfer and Pressure Distribution on Cone-Cylinder-Flare Configurations at Mach Five
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Wall heat transfer and flow field configuration of shock wave-turbulent boundary layer interactions on cryogenically cooled wall
Cryogenic wall cooling at 95 K shifts the separation point downstream in Mach 2 shock-turbulent boundary layer interactions and reduces local heat flux, enabled by cryogenic temperature-sensitive paint measurements.