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- Title
Wind Tunnel Testing of a Detonation Ramjet Model at Approach Air Stream Mach Number 5.7 and a Stagnation Temperature of 1500 K.
- 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.
- Abstract
The mode of continuous detonation combustion of hydrogen in the annular combustor of a model of a detonation air-breathing ramjet at the approach air stream Mach number 5.7 and a stagnation temperature of 1500 K was experimentally detected for the first time in a pulsed wind tunnel. The thrust and fuelbased specific impulse of the ramjet model were 1550 N and 3300 s, respectively.
- Subjects
SUPERSONIC aerodynamics; HYDROGEN; STAGNATION pressure; REYNOLDS number; GAS flow
- Publication
Doklady Physical Chemistry, 2018, Vol 481, Issue 1, p100
- ISSN
0012-5016
- Publication type
Article
- DOI
10.1134/S0012501618070035