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EVALUATION OF SHORT-DURATION ROCKET ENGINE TECHNIQUE FOR BASE HEAT TESTING WITH EXTERNAL AIRFLOW
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Base recirculation data were obtained on a 5.47--scale model of the Saturn 1-Block 2 booster at trajectory Mach numbers of 1.16 and 1.63. The rocket nozzle flow was produced by use of the short-duration combustor. The turbine exhaust gases were simulated by hydrogen. The test objectives were 1 to compare results obtained by the short-duration technique to those obtained by long-duration test methods and 2 to evaluate the operational advantages of the short-duration method as compared to other techniques. A comparison of model test to flight test data is also presented.
APPROVED FOR PUBLIC RELEASE