Hydrogen-fueled detonation ramjet model: Wind tunnel tests at approach air stream Mach number 5.7 and stagnation temperature 1500 K

The mode of continuous spinning detonation (CSD) combustion of hydrogen in the annular combustor of a model of a hydrogen-fueled detonation ramjet under conditions of approach air stream Mach number 5.7 and stagnation temperature 1500 K is registered experimentally in a short-duration (pulsed) wind...

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Bibliographic Details
Published in:International journal of hydrogen energy 2018-04, Vol.43 (15), p.7515-7524
Main Authors: Frolov, S.M., Zvegintsev, V.I., Ivanov, V.S., Aksenov, V.S., Shamshin, I.O., Vnuchkov, D.A., Nalivaichenko, D.G., Berlin, A.A., Fomin, V.M., Shiplyuk, A.N., Yakovlev, N.N.
Format: Article
Language:English
Subjects:
Detonation ramjet model
Fuel-based specific impulse
Pulsed detonation
Spinning detonation
Supersonic airflow
Wind tunnel
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Summary:The mode of continuous spinning detonation (CSD) combustion of hydrogen in the annular combustor of a model of a hydrogen-fueled detonation ramjet under conditions of approach air stream Mach number 5.7 and stagnation temperature 1500 K is registered experimentally in a short-duration (pulsed) wind tunnel at the overall air-to-hydrogen equivalence ratio (ER) ranging from 0.7 to 1.4. The maximum values of thrust and specific impulse of the ramjet model are attained at ER = 1.25 and are estimated as 1550 N and 3300 s, respectively. At 1.4 
ISSN:0360-3199
1879-3487
DOI:10.1016/j.ijhydene.2018.02.187