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Upstream porthole injection in a 2-D scramjet model

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Abstract.

Injection from portholes upstream of the combustion chamber was investigated as a method of delivering fuel into a scramjet. This method reduces the viscous drag on a model by allowing a reduction in the length of the combustion chamber. At experimental enthalpies of 3.0 MJ/kg in the T4 shock tunnel, there was no evidence of combustion in the intake, either by shadowgraph or pressure measurements. Combustion was observed in the combustion chamber. A theoretical extension of these results is made to a hot wall scenario.

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Authors and Affiliations

  1. Centre for Hypersonics, Department of Mechanical Engineering, The University of Queensland, St Lucia, 4072, Australia , , , , , , AU

    A.D. Gardner & A. Paull

  2. Centre for Hypersonics, Department of Physics, The University of Queensland, St Lucia, 4072, Australia , , , , , , AU

    T.J. McIntyre

Authors
  1. A.D. Gardner
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  2. A. Paull
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  3. T.J. McIntyre
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Received 2 January 2001 / Accepted 3 August 2001

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Gardner, A., Paull, A. & McIntyre, T. Upstream porthole injection in a 2-D scramjet model. Shock Waves 11, 369–375 (2002). https://doi.org/10.1007/s001930200120

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  • DOI: https://doi.org/10.1007/s001930200120

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