Thrust Performance of an Ideal Pulse Detonation Engine

摘要

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.