Experimental studies of an axisymmetric hydrogen-fueled detonation ramjet model 1.05-m 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 ranging from 4 to 8 with the total temperature of 290 K. In a supersonic air flow entering the combustor, continuous and longitudinally pulsating modes of hydrogen detonation with the corresponding characteristic frequencies of 1250 and 900 Hz were obtained. The maximum measured values of fuel-based specific impulse and total thrust were 3600 s and 2200 N. •Compact hydrogen-fueled detonation ramjet is designed and tested in wind tunnel.•1-m long 0.3-m i.d. ramjet comprises M5 air intake and expanding annular combustor.•Stable spinning and pulse modes of hydrogen detonation at M4 to M8 are obtained.•Total positive force of 100 N acting on ramjet at M8 has been registered for the first time.•Maximum fuel-based specific impulse of 3600 s is measured at M6.