In this paper, the effect of flight Mach number on the relative performance of pulse detonation engines and gas turbine engines is investigated. The effect of ram and mechanical compression on combustion inlet temperature and the subsequent sensible heat release is determined. Comparison of specific thrust, fuel consumption and impulse for the two engines show the relative benefits over the Mach number range.
Role of Air-Breathing Pulse Detonation Engines in High Speed Propulsion
52nd International Astronautical Congress ; 2001 ; Toulouse, France
2001-09-01
Preprint
No indication
English
Thermodynamics of air-breathing pulse-detonation engines
AIAA | 2001
|Pulse Detonation Engines for High Speed Flight
NTIS | 2002
|Pulse Detonation Engines for High Speed Flight
NTRS | 2002
|