Studies of shock/shock interaction on smooth and transpiration-cooled hemispherical nosetips in hypersonic flowExperimental studies are conducted to examine the utilization of transpiration cooling to reduce the peak-heating loads in areas of shock/shock interaction. Smooth and transpiration-cooled nosetip models, 12 inches in diameter, were employed in these studies, which focused on defining the pressure distributions and heat transfer in type III and IV interaction areas. Transpiration cooling was determined to significantly increase the size of the shock layer and to move the peak-heating point around the body. A transpiration-cooling rate of more than 30 percent of the freestream maximum flux did not lower the peak-heating level more than 10 percent, but the integrated heating loads were reduced.
Document ID
19910059011
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Holden, M. S. (Calspan Corp. Buffalo, NY, United States)
Rodriguez, K. M. (Calspan Corp. Buffalo, NY, United States)
Nowak, R. J. (NASA Langley Research Center Hampton, VA, United States)