Abstract
A panel code, capable of treating complete configurations, has been extended by an invers option. This means, that two types of patches may be present: ’design patches’, whose surface is derived from given pressures and ’analysis patches’, whose pressures are derived from given surface. To solve such ’mixed’ problems the panel code is embedded into an iteration loop, which minimizes the sum of squared pressure deviations. The geometry representation is done in terms of Bézier -splines with linear lofting. Intersections between wing- and body patches may occur. These are handled by locating a fictious design section inside the body and projecting it onto the body at a specified direction. Several examples demonstrate the power of the method and the usefulness to actual aircraft design problems.
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© 1997 Friedr. Vieweg & Sohn Verlagsgesellschaft mbH, Braunschweig/Wiesbaden
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Schwarten, H. (1997). Wing Design with a 3D-Subsonic Inverse Panel Method. In: Periaux, J., Bugeda, G., Chaviaropoulos, P.K., Labrujere, T., Stoufflet, B. (eds) EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics. Notes on Numerical Fluid Mechanics (NNFM), vol 55. Vieweg+Teubner Verlag. https://doi.org/10.1007/978-3-322-86570-0_4
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DOI: https://doi.org/10.1007/978-3-322-86570-0_4
Publisher Name: Vieweg+Teubner Verlag
Print ISBN: 978-3-322-86572-4
Online ISBN: 978-3-322-86570-0
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