Effect of roughness on heat transfer to hemisphere cylinders at Mach numbers 10.4 and 11.4
James C. Dunavant, Howard W. Stone, United States. National Aeronautics and Space Administration, Langley Research Center
National Aeronautics and Space Administration, 1967 - Technology & Engineering - 37 pages
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Ablation average heating boundary-layer displacement thickness calibration Davis H Diaconis effect of roughness Figure 17 figure 19 flow free-stream Reynolds number Heat-transfer and pressure heat-transfer distributions heating ratio heights of 0.63 Hemisphere Hemisphere Hemisphere hemisphere-cylinder models higher Reynolds numbers hypersonic inconel laminar boundary layer laminar heating Langley Research Center Mach 10.4 tests method of reference model model momentum thickness Reynolds NACA NASA TN numbers at transition orifices paper Present paper percent Present paper Present present tests presented in figure pressure distributions ratio of roughness reference 11 Reference 5 Reference Reynolds number range Rhudy and Magnan roughened models roughness elements roughness height roughness number ROUGHNESS ON HEAT roughness Reynolds number round protuberances shown in figure smooth model specific heats stagnation point stagnation pressure stagnation-point heat transfer Strass and Tyner surface area surface roughness temperature rise test Reynolds numbers thermocouple thickness Reynolds number transducers TRANSFER TO HEMISPHERE tunnel turbulent boundary layer