Experimental studies of an axisymmetric hydrogen-fueled detonation ramjet model 1.05-meter long and 0.31 m in diameter with an expanding annular combustor were performed in a pulse wind tunnel under conditions of approaching air stream Mach number M = 4, 5, 6 and 8 with the stagnation temperature T0 = 293 K and M = 5.7 with T0 = 1500 K. In a supersonic air flow entering the combustor, stationary continuous and longitudinally pulsating modes of hydrogen detonation were obtained depending on the test conditions. The maximum measured values of the fuel-based specific impulse were 3600 s for the tests with T0 = 293 K and 3300 s for the tests with T0 = 1500 K.
Hydrogen-fueled detonation ramjet model: Wind tunnel tests
V. S. Ivanov, S. M. Frolov, V. I. Zvegintsev, V. S. Aksenov, I. O. Shamshin, D. A. Vnuchkov, D. G. Nalivaichenko, A. A. Berlin, V. M. Fomin, A. N. Shiplyuk, N. N. Yakovlev; Hydrogen-fueled detonation ramjet model: Wind tunnel tests. AIP Conf. Proc. 2 November 2018; 2027 (1): 030041. https://doi.org/10.1063/1.5065135
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