Abstract
Quasi‐steady and two‐dimensional unsteady formulations of the problem on the operation cycle of a pulse detonation engine are derived. A formula for the specific impulse is obtained, and the thrust performance of the engine is calculated. It is found that the thrust performance of this engine for flight Mach numbers M ∈ [0; 3.6] and compression ratios p 2/p 1 ∈ [1; 80] are always higher than those of the ramjet and one‐spool turbojet. As the compression ratio increases, the advantage of the pulse detonation engine becomes less noticeable.
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Mitrofanov, V.V., Zhdan, S.A. Thrust Performance of an Ideal Pulse Detonation Engine. Combustion, Explosion, and Shock Waves 40, 380–385 (2004). https://doi.org/10.1023/B:CESW.0000033559.75292.8e
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DOI: https://doi.org/10.1023/B:CESW.0000033559.75292.8e