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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© 2003 Springer Science+Business Media Dordrecht
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Tulita, C., Raghunathan, S., Benard, E. (2003). Control of transonic periodic flow on NACA0012 aerofoil by contour bumps. In: Sobieczky, H. (eds) IUTAM Symposium Transsonicum IV. Fluid Mechanics and its Applications, vol 73. Springer, Dordrecht. https://doi.org/10.1007/978-94-010-0017-8_44
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DOI: https://doi.org/10.1007/978-94-010-0017-8_44
Publisher Name: Springer, Dordrecht
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