ANALYTICAL INVESTIGATION OF ROCKET ENGINE PERFORMANCE DEGRADATION DUE TO THE PRESENCE OF AN INERT DILUENT.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO
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The primary purpose of the investigation was to determine the degration of theoretical rocket engine performance which results from the introduction of nitrogen as an inert diluent into the oxidizer of the hydrogen-oxygen propellant combination. Also, the actual performance which can be attained in a rocket motor with such propellants was explored. A program for computation of theoretical performance was written for the IBM 1620 Data Processing System. The rocket performance parameters of characteristic velocity, thrust coefficient and specific impulse were calculated. Theoretical performance was computed and analyzed for chamber pressures of 300 and 150 psia at a nozzle area ratio of 4.001 over a range of mixture ratios from 0.15 to 0.50 of stoichiometric for nitrogen fractions of 0, 0.20, 0.40, 0.60 and 0.75. Characteristic velocity for a nitrogen fraction of 0.75 indicated a degradation to 60-63 of the pure oxygen value at the same equivalence ratio. Author