Abstract
This study reports the first experiments of a large-scale hydrogen-fueled oblique detonation engine model conducted in a hypersonic wind tunnel. The stabilization characteristic of oblique detonation wave, the specific combustion mode and the corresponding flow structures are emphasized. Results show that by adjusting the geometry of the combustor in different tests, two stabilized oblique detonation combustion modes relevant to the two theoretical branches of oblique detonation at a given wedge angle, referred to as the strong oblique detonation mode and the weak oblique detonation mode, respectively, are consequently implemented in the combustor.
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