NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Numerical Modeling of Pulse Detonation Rocket Engine Gasdynamics and PerformancePulse detonation engines (PDB) have generated considerable research interest in recent years as a chemical propulsion system potentially offering improved performance and reduced complexity compared to conventional gas turbines and rocket engines. The detonative mode of combustion employed by these devices offers a theoretical thermodynamic advantage over the constant-pressure deflagrative combustion mode used in conventional engines. However, the unsteady blowdown process intrinsic to all pulse detonation devices has made realistic estimates of the actual propulsive performance of PDES problematic. The recent review article by Kailasanath highlights some of the progress that has been made in comparing the available experimental measurements with analytical and numerical models.
Document ID
20040016354
Acquisition Source
Marshall Space Flight Center
Document Type
Other
Authors
Morris, C. I. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 7, 2013
Publication Date
December 12, 2003
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA Paper 2004-0463
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available