Abstract
“Adaptive Airfoil” is the title of an EREA project launched in January, 1998 with the participation of CIRA, DLR, FFA (now FOI), INTA and ONERA. The main objective of the project is to demonstrate the feasibility and to quantify the benefits of adaptive wing technology. Of the various ways to achieve wing adaptation, i.e. variable camber, suction/blowing, etc. the addition of surface bumps to the original airfoil geometry is an additional possibility. It has been shown recently that the combination of two bumps located at the position of the sonic line and close to the shock foot respectively leads to remarkable improvements with respect to drag reduction and buffet control. Research work in the field of aerodynamics of supercritical airfoils including dual bump systems has shown that beside of the location of the bumps along the upper wing surface, the fine tuning of shapes, height and their time dependent variations are of importance to successfully achieve the objectives. Numerical as well as experimental investigations have been carried out within the scope of the present project.
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References
Sobieczky, H., Seebass, A. R., “Supercritical Airfoil and Wing Design”, ANN. Rev. Fluid Mech. 16, pp.337–363, (1984).
Sobieczky, H., Geissler, W., “Active Flow Control Based on Transonic Design Concepts”, 17th AIAA Applied Aerodynamics Conference, June28–July1, 1999, Norfolk, VA.
Sobieczky, H., “Geometry Generator for Aerodynamic Design”, CISM Course and Lectures No. 366, ‘New Design Concepts for High Speed Air Transport’, Springer, Wien, New York (1997), pp.l37–158.
Geissler, W., “Instationäres Navier-Stokes Verfahren für beschleunigt bewegte Profile mit Ablösung (Unsteady Navier-Stokes Code for Accelerated Moving Airfoils with Separation)” in german, DLR-FB 92-03, (1992).
Geissler, W., Trenker, M., Sobieczky, H., “Active Dynamic Flow Control Studies on Rotor Blades”, Research and Technology Agency, Spring 2000 Symposium on Active Control Technology, Braunschweig, Germany, 8–12.May, 2000.
Spalart, P. R., Allmaras, S. R., “A One-Equation Turbulence Model for Aerodynamic Flows”, AIAA-Paper 92-0439, 1992.
Menter, F. R., “Improved two-equation k-omega Turbulence Models for Aerodynamic Flows”, NASA TM-103975, Oct.1992.
Rosemann, H., “The Cryogenic Ludwieg-Tube at Göttingen”, Special Course on Advances in Cryogenic Wind Tunnel Technology, AGARD-R-812, Cologne, Germany, 1996.
Beam, R., Warming, R. F., “An Implicit Factored Scheme for the Compressible Navier-Stokes Equations”, AIAA J., Vol.16, No.4, Apr.1978.
Geissler, W., Chandrasekhara, M. S., Platzer, M. F., Carr, L. W., “The Effect of Transition Modelling on the Prediction of Compressible Deep Dynamic Stall”, The Seventh Asian Congress of Fluid Mechanics, Dec.8–12, 1997, Chennai (Madras), India.
Geissler, W., Ruiz-Calavera, L. P., “Transition and Turbulence Modelling of Dynamic Stall and Buffet”, 4th International Symposium on Engineering Turbulence Modelling and Measurements”, Frantour&CCAS, Porticcio-Ajaccio, Corsica, France.
McDevitt, J. B., “Supercritical Flow About a Thick Circular Arc Airfoil”, NASA TM-78549, 1979.
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Geissler, W., Koch, S. (2003). Adaptive Airfoil. 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_46
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DOI: https://doi.org/10.1007/978-94-010-0017-8_46
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