Experimental flameholding performance of a scramjet cavity with an inclined front wall
نویسندگان
چکیده
This paper presents experimental data examining the flameholding performance of a scramjet cavity with an inclined front wall. Mach 8 flight-equivalent flows were delivered to axisymmetric, combustor via T4 reflected shock tunnel. The model was designed permit interchangeable geometries. Each examined maintained length-to-depth ratio 4, depth mm and close-out angle 22.5 deg. first possessed 90 deg wall/step, while second wall at 45 Ethylene fuel injected variety mass flow rates examine both scram-mode, jet-wake anchored dual-mode combustion, measurements obtained wall-mounted static pressure sensors. steady nature these combustion modes during tunnel test time demonstrated. Minimal differences in combustion-induced rises observed between two geometries across each fuelling condition. indicates that low pressure, quasi-stagnant region downstream step is not essential attaining robust flame-anchoring combustor. Chemically reacting, Reynolds-averaged Navier-Stokes computations performed for three dimensional Only minor mixing noted geometry/fuelling permutation. It retained more vortex structures within cavity, seeing complete breakdown structures. work could be further modified minimal impacts on performance.
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ژورنال
عنوان ژورنال: Aerospace Science and Technology
سال: 2022
ISSN: ['1626-3219', '1270-9638']
DOI: https://doi.org/10.1016/j.ast.2022.107622