Thrust stand testing is conducted on rotating detonation engines of various annular detonation channel widths and the impact of different scaling parameters on the performance of the devices is discussed. A focus is given in this work to identifying the relationship between the appropriate flow variables to facilitate comparison between geometries and the experimentally obtained specific impulses and specific thrusts, as well as an examination of stagnation pressure usage, through corrected thrust. Operation on both hydrogen and gaseous hydrocarbon fuel is presented. A comparison is made between the resulting propulsive performances found for similar rotating detonation engine geomtries.
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