Thrust performance of an ideal pulse detonation engine

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 $\mathrm{M}\in [0; 3.6]$ and compression ratios $p_2/p_1\in[1; 80]$ 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.