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Liquid Rotating Detonation Engine is one of the newest rocket engine for the near future propulsion system. This paper deals with revealing the phusical and engineering ptoblems, which has been difficulty with finding exprementally. This time we find out the thrust and specific impulse of LP-10/air RDE is 10% more than that of H2/air engines. Besides it is found out the quenching mechanism of JP-19/air detonation head.

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This page is a summary of: Numerical Study on JP-10/Air Detonation and Rotating Detonation Engine, AIAA Journal, March 2020, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/1.j058167.
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