27th Congress of International Council of the Aeronautical Sciences, 19 - 24 September 2010, Nice, France
Paper ICAS2010-4.3ST1

BOUNDARY LAYER COMBUSTION FOR VISCOUS DRAG REDUCTION IN PRACTICAL SCRAMJET CONFIGURATIONS

W. Y. K. Chan, D. J. Mee, M. K. Smart, J. C. Turner, R. J. Stalker
Univ. of Queensland, Australia

Keywords: boundary layer combustion, turbulent skin friction drag, drag reduction, flow non-uniformity, supersonic combustion

Boundary-layer combustion has been shown to be effective for reducing viscous drag in hypersonic flow. However, the implementation of boundary-layer combustion in realistic scramjet configurations can be affected by non-uniform flow entering the combustor. Experimental results showing the effects of flow non-uniformities on boundary-layer combustion will be presented.

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