Methane–oxygen mixture is an efficient propellant for rocket propulsion, and methane–oxygen driven rotating detonation engine has the potential to further increase the engine performance and rocket payload capacity. The rotating detonation propagation characteristics need systematic investigations due to the propellant unstable nature. In the present study, an experimental system is developed to conduct methane–oxygen rotating detonation experiments. The effect of injection scheme on the behavior of the methane–oxygen rotating detonation wave mode is examined. The propagation modes of rotating detonation wave are identified and analyzed by the dynamic pressure transducer and high-speed camera. Multi-wave co-propagating and counter-propagating modes are observed in the orifice-orifice impinging scheme. The wave propagation velocity decreases when the wave mode transits from co-propagating mode to counter-propagating mode. Decreasing the fuel orifice diameter leads to the growth in detonation wave front under the same condition, while the propagation velocity drops further. In the future work, methane–oxygen rotating detonation experiments under high pressure conditions will be conducted.