Experimental study of heat transfer to hypersonic nozzle walls
The heat transfer rate from a high enthalpy gas to the walls of a diverging nozzle, through which the gas was flowing, has been experimentally determined. The experimental results are compared with the predictions of several theories for the heat transfer through a laminar boundary layer from a high velocity gas flow. Theories for both reacting and non-reacting gases have been considered. An empirical equation which accounts for the conical flow effects is presented. Experimentally determined rates were found to be as much as ten times as large as predicted values. Discussion of the possible causes of disagreement is included. This discussion indicates the necessity for further investigation using surface temperature thermometers with rapid response, particularly near the nozzle throat. The need for reliable free stream property measurements is also indicated.
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