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Numerical and Experimental Examination of Shock Control Bump Flow Physics

In: High Performance Computing in Science and Engineering ‘12

Author

Listed:
  • K. Nübler

    (IAG Universität Stuttgart)

  • S. P. Colliss

    (University of Cambridge, Aerodynamics Laboratory)

  • T. Lutz

    (IAG Universität Stuttgart)

  • H. Babinsky

    (University of Cambridge, Aerodynamics Laboratory)

  • E. Krämer

    (IAG Universität Stuttgart)

Abstract

A method allowing a detailed investigation of the flow physics of shock control bumps (SCBs) on an unswept airfoil has been developed by comparison of the results of experiments and computations. A simple wind tunnel set-up is proposed which is shown to generate representative baseline conditions, allowing fine details of the flow to be measured using an array of techniques. Computational data for the same bump configuration is then validated against the experimental results, allowing a more intimate analysis of the flow physics as well as relating wind tunnel results to the performance of the SCB on an unswept wing.

Suggested Citation

  • K. Nübler & S. P. Colliss & T. Lutz & H. Babinsky & E. Krämer, 2013. "Numerical and Experimental Examination of Shock Control Bump Flow Physics," Springer Books, in: Wolfgang E. Nagel & Dietmar H. Kröner & Michael M. Resch (ed.), High Performance Computing in Science and Engineering ‘12, edition 127, pages 333-349, Springer.
    • Handle: RePEc:spr:sprchp:978-3-642-33374-3_25
    DOI: 10.1007/978-3-642-33374-3_25
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