AN INVESTIGATION OF BASE HEATING ON A 5.47-PERCENT-SCALE MODEL SATURN SA-1 BOOSTER AFTERBODY AT MACH NUMBERS 1.63 AND 3.07
ARO INC ARNOLD AFS TN
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An investigation was conducted to determine the base recirculation characteristics of several different turbine exhaust ducts on a 5.47 scale model of the Saturn SA-1 booster afterbody. Hydrogen gas was used to simulate the combustible products of the turbine exhaust. Base heating and base pressure data were taken with external airflow at Mach numbers 1.63 33,000 to 45,000-ft altitude and 3.07 70,000 to 80,000ft altitude. The data indicated no base burning resulting from circulation of the combustible turbine exhaust gases. Flame shield calorimeter data indicated the maximum heat transfer rate at the center of the shield to be 113 Btusq ftsec. Flame shield pressure data indicated that the flow out from the flame shield region between adjacent engines became sonic at approximately 60,000-ft altitude.