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Pulse Detonation Engines for High Speed FlightRevolutionary concepts in propulsion are required in order to achieve high-speed cruise capability in the atmosphere and for low cost reliable systems for earth to orbit missions. One of the advanced concepts under study is the air-breathing pulse detonation engine. Additional work remains in order to establish the role and performance of a PDE in flight applications, either as a stand-alone device or as part of a combined cycle system. In this paper, we shall offer a few remarks on some of these remaining issues, i.e., combined cycle systems, nozzles and exhaust systems and thrust per unit frontal area limitations. Currently, an intensive experimental and numerical effort is underway in order to quantify the propulsion performance characteristics of this device. In this paper, we shall highlight our recent efforts to elucidate the propulsion potential of pulse detonation engines and their possible application to high-speed or hypersonic systems.
Document ID
20020082902
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Povinelli, Louis A. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
September 1, 2002
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA/TM-2002-211908
Paper-17-5169
E-13598
NAS 1.15:211908
Meeting Information
Meeting: 11th International American Inst. of Aeronautics and Astronautics and Association Aeronautique et Astronautique de France Conference
Location: Orleans
Country: France
Start Date: September 29, 2002
End Date: October 4, 2002
Sponsors: Association Aeronautique et Astronautique de France, American Inst. of Aeronautics and Astronautics
Funding Number(s)
PROJECT: RTOP 706-21-33-07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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