Abstract
In this work airfoil and wing design results using a sectional conical wing method for analysis and design are presented. This method allows the design of swept tapered wing sections. It is useful for transonic Natural Laminar Flow (NLF) design, where sweep and tapering of the wing has to be taken into account. In the first part of this work a transonic tapered wing NLF airfoil catalogue was generated. Different airfoils were designed by varying the design Mach and Reynolds numbers, lift coefficient, leading-edge sweep and airfoil thickness. In the second part a NLF wing was designed for a short range aircraft wing-body configuration. Using the airfoils from the catalogue a wing was obtained with an acceptably large transition region and small shocks on the upper side. Due to the fuselage influence the inner lower wing required further design. For this purpose a 3D inverse design method was used.
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Acknowledgments
The research leading to these results has received funding from the European Union’s Seventh Framework Programme (FP7/2007-2013) for the Clean Sky Joint Technology Iniative under grant agreement number CSJU-GAM-SWFA-2008-001.
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von Geyr, J.F., von Hatzbach, F.K.z., Seitz, A., Streit, T., Wichmann, G. (2014). Wing Design Based on a Tapered Wing Natural Laminar Flow Airfoil Catalogue. In: Dillmann, A., Heller, G., Krämer, E., Kreplin, HP., Nitsche, W., Rist, U. (eds) New Results in Numerical and Experimental Fluid Mechanics IX. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 124. Springer, Cham. https://doi.org/10.1007/978-3-319-03158-3_19
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DOI: https://doi.org/10.1007/978-3-319-03158-3_19
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