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Numerical Analysis of a Rotating Detonation Engine in the Relative Reference FrameA two-dimensional, computational fluid dynamic (CFD) simulation of a semi-idealized rotating detonation engine (RDE) is described. The simulation operates in the detonation frame of reference and utilizes a relatively coarse grid such that only the essential primary flow field structure is captured. This construction yields rapidly converging, steady solutions. Results from the simulation are compared to those from a more complex and refined code, and found to be in reasonable agreement. The performance impacts of several RDE design parameters are then examined. Finally, for a particular RDE configuration, it is found that direct performance comparison can be made with a straight-tube pulse detonation engine (PDE). Results show that they are essentially equivalent.
Document ID
20140013391
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Paxson, Daniel E.
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
November 6, 2014
Publication Date
March 1, 2014
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-18837
NASA/TM-2014-216634
GRC-E-DAA-TN12556
AIAA Paper 2014-0284
Meeting Information
Meeting: Science and Technology Forum and Exposition (SciTech2014):
Location: National Harbor, MD
Country: United States
Start Date: January 13, 2014
End Date: January 17, 2014
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 794072.02.03.05.04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
propulsion
pulse detonation engines
Combustion
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