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 < ER < 1.6, the mode of longitudinally pulsating detonation (LPD) combustion is registered with somewhat lower values of thrust and specific impulse. •Hydrogen-fueled detonation ramjet is tested in wind tunnel at M5.7 and Tst = 1500 K.•1-m long 0.3-m i.d. ramjet comprises M5 air intake and expanding annular combustor.•Stable spinning detonation mode is obtained at fuel-to-air ratios from 0.7 to 1.4.•Stable pulsed detonation mode is obtained at fuel-to-air ratios from 1.4 to 1.6.•Maximum fuel-based specific impulse above 3000 s and thrust above 1500 N are measured.