Detonation Wave Hypersonic Ramjet

Performance of a hypersonic ramjet having a detonation wave combustion process is described. Flight speeds from Mach 2.5 to 10 are examined. Thermodynamic property changes across a detonation wave are presented. Engine cycle performance characteristics are computed including air specific impulse, specific fuel consumption and thermal efficiency. The effect of component efficiency on cycle performance is examined and the opt imum place in the cycle for the detonation wave is found. The subsonic burning ramjet is shown always to have superior thermodynamic performance compared to a detonation wave engine, but the differences are often minor. Other differences and some design features are discussed.