Abstract
Originally developed as a flow control device Shock Control Bumps (SCB) reduce wave drag of an aircraft wing at off-design in transonic speed effectively. Recently, another field of application for such bumps has been studied, namely the delay and alleviation of buffet, an unsteady shock motion due to continuous flow separation and re-attachment at the rear part of the airfoil. In principle the idea of buffet alleviation is the use of SCB as a sort of ‘smart’ vortex generator. Considerable effort has been undertaken to link geometrical bump features to buffet affecting flow characteristics. In this paper a parametric study on the influence of flank shape of a three-dimensional wedge-shaped SCB on its performance and buffet behavior is presented. It has been found that performance as well as buffet behavior can be improved by optimization of the bump flanks. The study shows that length of front and rear flank should be increased up to given constraints (e.g. flaps on a wing or inserts for a wind tunnel model) and a narrow front and wide rear flank increase c L, max and damp lift oscillations at buffet onset.
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Acknowledgements
This study is undertaken within the European-Russian project BUTERFLI, supported by the European FP7 program (FP7-AAT-2013.8-1-RTD-RUSSIA) under Grant Agreement no. 605605.
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Mayer, R., Zimmermann, D., Wawrzinek, K., Lutz, T., Krämer, E. (2016). Numerical Study of Three-Dimensional Shock Control Bump Flank Effects on Buffet Behavior. In: Nagel, W., Kröner, D., Resch, M. (eds) High Performance Computing in Science and Engineering ’15. Springer, Cham. https://doi.org/10.1007/978-3-319-24633-8_32
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DOI: https://doi.org/10.1007/978-3-319-24633-8_32
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