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- W2139475858 abstract "Abstract : An investigation was made to determine the effects of postrun cooling at simulated altitude pressures on ablative-rocket- material ablating characteristics. Two identical ablative nozzles were test fired six times each (40-sec tests) on the end of a 150-pound-thrust hydrogen-oxygen rocket engine at an absolute chamber pressure of 100 pounds per square inch. One nozzle cooled after each test in an ambient-pressure environment; the other nozzle cooled after each test while subjected to low-pressure vacuum conditions. The results are expressed in terms of nozzle weight 1055, char-layer thickness, and internal-dimension changes. Under the conditions of these tests, little noticeable effect occurred on the rates at which ablation materials erode either at sea-level pressures or at low pressures. in about 4 minutes of running, the throat area of each nozzle had essentially doubled, and the char was about 1/4 inch thick." @default.
- W2139475858 created "2016-06-24" @default.
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- W2139475858 date "1963-06-01" @default.
- W2139475858 modified "2023-09-27" @default.
- W2139475858 title "EXPERIMENTAL INVESTIGATION OF ROCKET-ENGINE ABLATIVE - MATERIAL PERFORMANCE AFTER POSTRUN COOLING AT ALTITUDE PRESSURES" @default.
- W2139475858 hasPublicationYear "1963" @default.
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