Enviar artigo por via de e-mail Thrust characteristics of an airbreathing pulse detonation engine in flight at mach numbers of 0.4 to 5.0
- Autores: Zangiev A.E.1,2,3, Ivanov V.S.1,2,3, Frolov S.M.1,2,3
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Afiliações:
- Semenov Institute of Chemical Physics
- Center of Pulse Detonation Combustion
- National Nuclear Research University “MEPhI,”
- Edição: Volume 10, Nº 2 (2016)
- Páginas: 272-283
- Seção: Combustion, Explosion, and Shock Waves
- URL: https://journals.rcsi.science/1990-7931/article/view/197453
- DOI: https://doi.org/10.1134/S1990793116020135
- ID: 197453
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Resumo
Multidimensional calculations are performed to demonstrate that, by its characteristics, the pulse detonation engine (PDE) is a unique type of ramjet propulsion system, which can be used in both subsonic and supersonic aircraft. By a number of examples, it is shown that, in various thrust characteristics, such as the specific impulse, specific fuel consumption, and specific thrust, the PDE substantially exceeds ramjet engines.
Sobre autores
A. Zangiev
Semenov Institute of Chemical Physics; Center of Pulse Detonation Combustion; National Nuclear Research University “MEPhI,”
Email: smfrol@chph.ras.ru
Rússia, Moscow; Moscow; Moscow
V. Ivanov
Semenov Institute of Chemical Physics; Center of Pulse Detonation Combustion; National Nuclear Research University “MEPhI,”
Email: smfrol@chph.ras.ru
Rússia, Moscow; Moscow; Moscow
S. Frolov
Semenov Institute of Chemical Physics; Center of Pulse Detonation Combustion; National Nuclear Research University “MEPhI,”
Autor responsável pela correspondência
Email: smfrol@chph.ras.ru
Rússia, Moscow; Moscow; Moscow
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