Summary
The objective of the present study was, similar to the work of EADS-Airbus D described in the preceding chapter, to apply shock and boundary layer control to an A340-type aircraft wing of existing turbulent design and to determine benefits and penalties of control implementation on the operational aircraft. The control mechanism considered was foremost the contour bump. (Originally, also a new turbulent wing design with integrated bump should have been considered; however, this task was not performed due to time limitations.)
The full contribution was, unfortunately, not available for inclusion into the present volume. The reader is requested to accept our apologies and to refer to Chapter 6 for an overview and essential results of the work performed. A brief summary is given below.
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© 2002 Springer-Verlag Berlin Heidelberg
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Doe, R. (2002). Assessment of Bump Control and its Application to a Long-range Turbulent-wing Aircraft. In: Stanewsky, E., Délery, J., Fulker, J., de Matteis, P. (eds) Drag Reduction by Shock and Boundary Layer Control. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM), vol 80. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-45856-2_14
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DOI: https://doi.org/10.1007/978-3-540-45856-2_14
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-07762-3
Online ISBN: 978-3-540-45856-2
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