AN EXPERIMENTAL INVESTIGATION OF NOZZLE COOLING FOR A SMALL ROCKET ENGINE
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
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An investigation was made to determine experimentally the effect of film-cooling a rocket engine nozzle with a reactant gas. Coolant quantities, injection velocities and angles, and axial injection location were varied to determine the conditions under which adequate film cooling could be achieved. Five basic coolant configurations consisting of three De Laval type nozzles and three coolant chamber liners provided coolant injection at the nozzle entrance andor near the nozzle throat. Decreasing the injection velocity resulted in increased wall temperature reductions so that critical areas of the nozzle could be adequately film cooled.