Combustion Processes in Liquid Propellant Rocket Motors.
Final rept. 1 Sep 65-31 Aug 68,
PRINCETON UNIV NJ DEPT OF AEROSPACE AND MECHANICAL SCIENCES
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This research is concerned with the details of rocket combustion processes and how fundamental physical, chemical and aerodynamic approaches give insight to these details. These fundamental approaches are oriented to give specific basic knowledge about combustion instability in rockets and the important parameters which govern such instabilities and about chemical kinetic aspects of propellant systems and the relationship of kinetics to the over-all combustion process, instability problem, propellant sensitivity, etc. One aspect is directed towards understanding the gas phase contribution to high-frequency combustion instability. The investigation employs rockets using premixed gaseous propellants and a non-linear shock wave instability analysis. These gas rockets eliminate those phenomena peculiar to condensed phase systems and thus the instabilities can be attributed to gas phase phenomena, mainly chemical kinetics. Another aspect seeks to understand the high temperature homogeneous gas phase reaction kinetics of propellants. Author
- Combustion and Ignition
- Liquid Propellant Rocket Engines