Summary
To increase the aerodynamic performance of airfoils at different transonic flight conditions computational and experimental investigations for an airfoil with an adaptive upper side geometry were initiated. The main objective is to improve the lift-to-drag ratio by adapting the upper airfoil surface using numerical optimization such that the extent of the laminar boundary layer is enlarged without the occurrence of a separation bubble. Unlike in most airfoil optimization procedures the transition location is not fixed but is determined numerically using the semi-empirical e N-method based on the linear stability theory. To verify the numerical results it is necessary to perform experiments with natural transition on a laminar-type airfoil at transonic mean flow conditions. The transition location and the separation area are determined at transonic speeds in the trisonic wind tunnel with an adaptive wall test section using the hot-film method with a 20 sensor array as well as the liquidcrystal technique. The methods will also be applied to a future airfoil model with an adaptive upper side geometry to experimentally verify the result of the numerical optimization.
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Meijering, A., Limberg, W., Schröder, W. (2003). Aerodynamic Design of Transonic Adaptive Airfoils with Natural Transition. In: Ballmann, J. (eds) Flow Modulation and Fluid—Structure Interaction at Airplane Wings. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 84. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-44866-2_5
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DOI: https://doi.org/10.1007/978-3-540-44866-2_5
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