Standing stability enhancement method of oblique detonation waves in a confined space and its experimental validation

Hypersonic ramjets with the combustion mode of oblique detonation are promising in the high-Mach-number air-breathing propulsion field. It is very important to overcome the standing stability problem of oblique detonation waves for realizing this technical scheme. A standing stability enhancement method of oblique detonation waves in a confined space is proposed and validated in a direct-connect experiment under the Ma 8.0 near-real condition. Supersonic premixed gases are produced by using array nozzles and a non-reacting gas layer is formed by cutting off the fuel supply in the near-wall nozzle units. After the oblique detonation wave enters the near-wall region, it decays to an inert shock wave due to the presence of the non-reaction gas layer and therefore its Mach reflection on the wall can be significantly weakened to avoid choking flow. Through this method, the standing stability of oblique detonation waves is well enhanced and a long-time standing oblique detonation wave is obtained under the near-real condition.