Knowledge of rate of heat transfer to walls of supersonic nozzles is desirable for design of rocket nozzles and of hypersonic wind tunnel nozzles; heat transfer to such nozzle is boundary layer problem with variable free stream velocity; approximate solution given for case of turbulent boundary layer.
Heat transfer to incompressible turbulent boundary layer and estimation of heat-transfer coefficients at supersonic nozzle throats
J Aeronautical Sciences
Journal of the Aeronautical Sciences ; 23 , n 2
1956
11 pages
Article (Journal)
English
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