AIR-FILM COOLING OF A SUPERSONIC NOZZLE

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Abstract
An experimental study was made of the internal air-film cooling of a Mach 2.4, nonadiabatic wall, axially symmetric nozzle. The main stream air was heated to supply temperatures from 672 to 1212 R at supply pressures from 115 to 465 psia. The film coolant air was injected through a single peripheral slot at an angle of 10 degrees from the nozzle wall. The coolant-to-main stream mass flow ratios were varied up to 20%. Steady-state nozzle wall temperatures were measured in both the subsonic and the supersonic flow regimes. The turbulent pipe flow equation of Dittus and Boelter was found to be applicable in predicting the heat transfer rates in the absence of film cooling. A modified version of the semi-empirical equation of Hatch and Papell was found applicable in estimating the filmcooled nozzle wall temperatures. (Author)

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