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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