Control of transonic periodic flow on NACA0012 aerofoil by contour bumps
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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- 1.Stanewsky, E., Fulker, J., Delery, J., Geibler, J., “Drag Reduction by passive Shock Control-Results of the project EUROSHOCK, AER2-CT92-0049”, Notes on Num. Fluid Mech., Vol 56, Vieweg Verlag, 1997.Google Scholar
- 2.Delery, J., “Flow physics involved in shock wave/boundary layer interaction control”, IUTAM Symposium on Mechanics of Passive and Active Flow Control, Gottingen, Germany, pp. 15–22, 1998.Google Scholar
- 3.Ashill, P.R., Fulker, J., Shires, A., “A novel technique for controlling shock strength of laminar-flow aerofoil sections”, Proceed of the First European Forum on Laminar Flow Technology, DGLR-Bericht 92-06, 1992.Google Scholar
- 5.Edwards, J., “Transonic shock oscillations calculated with a new interactive boundary layer coupling method”, AIAA Paper 93-0777, 1993.Google Scholar
- 7.Tijdeman, H., “Investigation of the Transonic Flow Around Oscillating Airfoils”, National Aerospace Lab., The Netherlands, NLR TR-77-090U, 1977.Google Scholar