Thrust Performance of an Ideal Pulse Detonation Engine |
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Authors: | V. V. Mitrofanov S. A. Zhdan |
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Affiliation: | (1) Lavrent'ev Institute of Hydrodynamics, Siberian Division, Russian Academy of Sciences, Novosibirsk, 630090 |
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Abstract: | Quasisteady and twodimensional 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 p2/p1 [1; 80] are always higher than those of the ramjet and onespool turbojet. As the compression ratio increases, the advantage of the pulse detonation engine becomes less noticeable. |
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Keywords: | detonation pulsed detonation engine thrust performance |
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