Experimental Investigation of Rocket-Engine Ablative-Material Performance After Postrun Cooling at Altitude Pressures
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CENTER
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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 14 inch thick.
- Miscellaneous Materials
- Rocket Engines