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This study experimentally investigated the use of a Shchelkin spiral obstacle in a pulse detonation rocket engine operating at frequencies between 4.4-20 Hz. Pressure transducers measured the detonation waves as they propagated through the engine. Results showed the engine was capable of repetitive pulsed operation. Pressure profiles through the spiral indicated deflagration to detonation transition occurred, though peak pressures were lower than theoretical values due likely to poor fuel-oxidizer mixing an

Author

Mohammad Kalamuddin

Language

EN