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.
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