Shock/shock interference on a transpiration cooled hemispherical modelExperimental results are presented which show the effectiveness of transpiration cooling in reducing the peak heat flux caused by an impinging shock on a bow shock of a hemispherical model. The 12-inch diameter hemispherical transpiration model with helium coolant was tested in the Calspan 48-inch Hypersonic Shock Tunnel at nominal Mach 12.1 and freestream unit Reynolds number of 0.33 x 10 to the 6th/ft. An incident shock wave, generated by a blunt flat-plate shock generator inclined at 10 deg to the freestream, intersected the bow shock of the model to produce shock/shock interference. The stagnation heat flux without coolant or shock/shock interference was about 1.6 times a smooth surface laminar prediction due to effective roughness of the coolant ejection slots. A coolant mass flux 31 percent of the freestream mass flux reduced the stagnation heat flux to zero without shock/shock interference. However, for the same coolant mass flux and with shock/shock interference the peak heat flux was only reduced 8.3 percent, even though the total integrated heat load was reduced.
Document ID
19900051716
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nowak, Robert J. (NASA Langley Research Center Hampton, VA, United States)
Wieting, Allan R. (NASA Langley Research Center Hampton, VA, United States)
Holden, Michael S. (Calspan Corp. Buffalo, NY, United States)