Air Force Materiel Command REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704-0188The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. 1. REPORT DATE (DD-MM-YYYY)2. REPORT TYPE (From -To) Final Technical DATES COVERED SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)AF Office of Scientific Research 875 N. Randolph St. Room 3112 Arlington, VA 22203 SPONSOR/MONITOR'S ACRONYM(S) AFOSR SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTApproved for Public Release; Distribution Unlimited SUPPLEMENTARY NOTES ABSTRACTThe goal of the project was to understand how changes in the rate of energy addition can be used to alter the combustion instability characteristics of liquid rocket engines. Fuels with increased energy, either due to higher heats of formation or energetic additives, presumably result in higher performance. This study seeks to understand how changes in combustion rate, due to fuel chemistry changes, might be used to develop high-performing, stable rocket engines. The overall objective of the project was to develop a fundamental understanding of how the spatial distribution of combustion and its temporal response to pressure oscillations depends on kinetic rates, flammability limits, and energy release density. The study combines basic drop combustion experiments, an in situ study using a spontaneously unstable model rocket combustor, and associated modeling of particles in combustion chamber gas flows. SUBJECT TERMSenergetic propellants, combustion stability, particulate dynamics FUEL CHEMISTRY AND COMBUSTION DISTRIBUTION EFFECTS ON ROCKET ENGINE COMBUSTION STABILITYThe goal of the project was to understand how changes in the rate of energy addition can be used to alter the combustion instability characteristics of liquid rocket engines. Fuels with increased energy, either due to higher heats of formation or energetic additives, presumably result in higher performance. This study seeks to understand how changes in combustion rate, due to fuel chemistry changes, might be used to develop high-performing, stable rocket engines. The overall objective of the project was to develop a fundamental understanding of how the spatial distri...
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