Abstract
This work deals with the development of a system-performance and thermodynamic-cycle analysis for air-breathing pulse detonation engines (PDE), to facilitate the design optimization at minimal computational expense. A modular approach is established to study all the essential parts of an engine including inlet, combustion chamber with multiple detonation tubes, and nozzle. The effects of all known processes on engine performance are studied systematically, and the various mechanisms responsible for performance loss are identified. Finally, the influence of exhaust nozzle design on engine propulsive efficiency is discussed.
Original language | English |
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Publication status | Published - 2002 |
Event | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States Duration: 2002 Jan 14 → 2002 Jan 17 |
Conference
Conference | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 |
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Country/Territory | United States |
City | Reno, NV |
Period | 02-01-14 → 02-01-17 |
All Science Journal Classification (ASJC) codes
- Space and Planetary Science
- Aerospace Engineering