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Progress in the Development of a Nozzle Design Methodology for Pulsed Detonation EnginesThe Johns Hopkins University Applied Physics Laboratory (JHU/APL), in support of the NASA Glenn Research Center (NASA GRC), is investigating performance methodologies and system integration issues related to Pulsed Detonation Engine (PDE) nozzles. The primary goal of this ongoing effort is to develop design and performance assessment methodologies applicable to PDE exit nozzle(s). APL is currently focusing its efforts on a common plenum chamber design that collects the exhaust products from multiple PDE tubes prior to expansion in a single converging-diverging exit nozzle. To accomplish this goal, a time-dependent, quasi-one-dimensional analysis for determining the flow properties in and through a single plenum and exhaust nozzle is underway. In support of these design activities, parallel modeling efforts using commercial Computational Fluid Dynamics (CFD) software are on-going. These efforts include both two and three-dimensional as well as steady and time-dependent computations to assess the flow in and through these devices. This paper discusses the progress in developing this nozzle design methodology.
Document ID
20020073121
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Leary, B. A.
(Johns Hopkins Univ. Laurel, MD United States)
Waltrup, P. J.
(Johns Hopkins Univ. Laurel, MD United States)
Rice, T.
(Johns Hopkins Univ. Laurel, MD United States)
Cybyk, B. Z.
(Johns Hopkins Univ. Laurel, MD United States)
Date Acquired
August 20, 2013
Publication Date
April 1, 2002
Publication Information
Publication: 26th JANNAF Airbreathing Propulsion Subcommittee Meeting
Volume: 1
Subject Category
Aircraft Propulsion And Power
Funding Number(s)
CONTRACT_GRANT: NAG3-2569
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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