Reduction of surface friction drag in scramjet engine by boundary layer combustion
نویسندگان
چکیده
This study investigates the effects of boundary layer combustion on skin friction reduction in a model scramjet combustor. The 4-equation RANS (Transition SST model) is employed as turbulence and one experimental case which involves supersonic turbulent used for validating numerical simulation method. Then wall jet device can be to inject hydrogen into designed added lower combustor engine. results showed that optimal ratio between primary fuel, producing thrust, drag reduction, getting largest skin-friction when installing combustor, 3:1. modifying location setting position too close upstream or downstream could not get maximum overall reduction. installation flow path depends coupling fuel combustion. In practical design, distribution should weighed improve efficiency engine performance.
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ژورنال
عنوان ژورنال: Aerospace Science and Technology
سال: 2021
ISSN: ['1626-3219', '1270-9638']
DOI: https://doi.org/10.1016/j.ast.2021.106788