Email this article Thrust characteristics of an airbreathing pulse detonation engine in flight at mach numbers of 0.4 to 5.0
- Authors: Zangiev A.E.1,2,3, Ivanov V.S.1,2,3, Frolov S.M.1,2,3
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Affiliations:
- Semenov Institute of Chemical Physics
- Center of Pulse Detonation Combustion
- National Nuclear Research University “MEPhI,”
- Issue: Vol 10, No 2 (2016)
- Pages: 272-283
- Section: Combustion, Explosion, and Shock Waves
- URL: https://journal-vniispk.ru/1990-7931/article/view/197453
- DOI: https://doi.org/10.1134/S1990793116020135
- ID: 197453
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Abstract
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.
About the authors
A. E. Zangiev
Semenov Institute of Chemical Physics; Center of Pulse Detonation Combustion; National Nuclear Research University “MEPhI,”
Email: smfrol@chph.ras.ru
Russian Federation, Moscow; Moscow; Moscow
V. S. Ivanov
Semenov Institute of Chemical Physics; Center of Pulse Detonation Combustion; National Nuclear Research University “MEPhI,”
Email: smfrol@chph.ras.ru
Russian Federation, Moscow; Moscow; Moscow
S. M. Frolov
Semenov Institute of Chemical Physics; Center of Pulse Detonation Combustion; National Nuclear Research University “MEPhI,”
Author for correspondence.
Email: smfrol@chph.ras.ru
Russian Federation, Moscow; Moscow; Moscow
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