Abstract <p>Kulite XTEH-10L-190 (M) Series high-frequency pressure sensors are applied to record pressure traces in a transverse detonation wave propagating in an annular cylindrical combustor during continuous spin detonation of a hydrogen–air mixture. Pressure levels are determined at the detonation wave front in an air manifold and at the combustor outlet relative to the time-averaged static pressure recorded by Trafag low-frequency sensors (10 kHz). Pressure fluctuations behind the wave front indicate complex gas dynamics in its vicinity. A chemical reaction region is identified behind the wave front, accounting for approximately 6.3% of the interwave period. A decrease in the minimum equivalence ratio is observed with increasing combustor pressure to 0.22, at which point continuous spin detonation develops. The velocities of transverse detonation waves drops with decreasing equivalence ratio and approach the ideal Chapman–Jouguet detonation velocity under certain conditions. Based on the total and static pressure readings at the combustor outlet, the specific impulse is calculated; when the cold-flow thrust is subtracted, its maximum value is 5000 s at an excess equivalence ratio of 0.35. It is shown that the total pressure loss during air exhaust from the manifold into the combustor through a 6-mm gap (critical flow regime) is 4 to 5% higher than during subcritical exhaust through a 10-mm gap.</p>