Computational and Experimental Study of Nozzle Performance for Rotating Detonation Rocket Engines
Author:
Affiliation:
1. Purdue University, West Lafayette, Indiana 47907
2. NASA Marshall Space Flight Center, Huntsville, Alabama 35812
Funder
NASA Space Technology Research Grant
Air Force Office of Scientific Research
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.B38244
Reference31 articles.
1. Rotating Detonation Wave Propulsion: Experimental Challenges, Modeling, and Engine Concepts
2. Experimental research on the rotating detonation in gaseous fuels–oxygen mixtures
3. Rotating Detonation Engine Performance Model for Rocket Applications
4. Effects of Diverging Nozzle Downstream on Flow Field Parameters of Rotating Detonation Combustor
5. The effect of the throat width of plug nozzles on the combustion mode in rotating detonation engines
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