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Control of transonic periodic flow on NACA0012 aerofoil by contour bumps

  • C. Tulita
  • S. Raghunathan
  • E. Benard
Part of the Fluid Mechanics and its Applications book series (FMIA, volume 73)

Abstract

The adaptive wing concept of Contour Bumps is numerically investigated for drag reduction and extending the buffet boundary in transonic periodic flows. The periodic shock oscillations are initiated on a NACA0012 adapted aerofoil by moving the aerofoil from a regime of steady transonic flow into a regime of periodic flow by a change in airflow incidence. The results indicate a damping of shock oscillations and a viscous drag reduction of 7.5% in the case when a Contour Bump was positioned underneath the shock.

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Copyright information

© Springer Science+Business Media Dordrecht 2003

Authors and Affiliations

  • C. Tulita
    • 1
  • S. Raghunathan
    • 1
  • E. Benard
    • 1
  1. 1.School of Aeronautical EngineeringThe Queen’s University of BelfastBelfastUK

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