An Investigation of Base Heating with a 5.47-Percent Saturn SA-1 Booster Model at Mach Numbers 0.8 and 1.15
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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An investigation was conducted to determine the base recirculation characteristics of the simulated propellant pump turbine exhaust gases of a 5. 47- scale model of the SA-1 Saturn afterbody. Gaseous hydrogen was used to simulate the combustible turbine exhaust gas of the fullscale missile. Base heating and pressure data were obtained at simulated flight trajectory conditions of M0.8 0.816,000-ft and M1.15 1.1527,500-ft using several turbine exhaust duct configurations. In addition, the effect on base heating with one engine inoperative, of variation in turbine exhaust gas momen um, of finned-model operation, of variation in engine OF ratio, and of variation in altitude was investigated. At both simulated flight trajectory conditions, the lowest base heating rates were obtained using a streamlined turbine exhaust duct configuration. The following conditions reduced base heating, based on data obtained with the long turbine exhaust ducts operation with one engine inoperative, increased turbine exhaust gas discharge momentum, and increased engine OF ratio.
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