An experimental investigation was carried out to appraise the effect of swirl on heat transfer in the laminar boundary layer development region in a highly cooled tube and nozzle. The ratio of gas-side wall-temperature-to-stagnation-temperature ranged from 0.095 to 0.135. In the swirling flow of argon with ratio of peak-tangential-velocity-to-axial velocity of 3.6 at the injection port, the level of heat transfer to the tube wall was increased from 200 to 60 percent above the level without swirl. In the swirling flows, the wall heat flux level was significantly higher in the tube than in the nozzle downstream. Because of the relatively high heat transfer to the wall, there were appreciable reductions in stagnation enthalpy in the flows that spanned a range of Reynolds numbers from about 360 to 500.
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Heat Transfer From a Very High Temperature Laminar Gas Flow With Swirl to a Cooled Circular Tube and Nozzle
L. H. Back,
L. H. Back
Jet Propulsion Laboratory, California Institute of Technology, Pasadena, CA 91109
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P. F. Massier
P. F. Massier
Jet Propulsion Laboratory, California Institute of Technology, Pasadena, CA 91109
Search for other works by this author on:
L. H. Back
Jet Propulsion Laboratory, California Institute of Technology, Pasadena, CA 91109
P. F. Massier
Jet Propulsion Laboratory, California Institute of Technology, Pasadena, CA 91109
J. Heat Transfer. Feb 1994, 116(1): 35-39 (5 pages)
Published Online: February 1, 1994
Article history
Received:
January 1, 1992
Revised:
April 1, 1993
Online:
May 23, 2008
Citation
Back, L. H., and Massier, P. F. (February 1, 1994). "Heat Transfer From a Very High Temperature Laminar Gas Flow With Swirl to a Cooled Circular Tube and Nozzle." ASME. J. Heat Transfer. February 1994; 116(1): 35–39. https://doi.org/10.1115/1.2910880
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