Abstract
A method allowing a detailed investigation of the flow physics of shock control bumps (SCBs) on an unswept airfoil has been developed by comparison of the results of experiments and computations. A simple wind tunnel set-up is proposed which is shown to generate representative baseline conditions, allowing fine details of the flow to be measured using an array of techniques. Computational data for the same bump configuration is then validated against the experimental results, allowing a more intimate analysis of the flow physics as well as relating wind tunnel results to the performance of the SCB on an unswept wing.
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Notes
- 1.
The perspective view in (b) is used as the oil accumulated at the foci in the wind tunnel experiment was smeared by tunnel shutdown, obscuring the topology. This image was taken from a high-definition video recorded during the tunnel run.
References
Stanewsky, E., Délery, J., Fulker, J. and de Matteis, P., Drag reduction by shock boundary layer control, Vol 80 of: Notes on Numerical Fluid Mechanics and Multidisciplinary Design, Springer Verlag, 2002.
Pätzold, M., Auslegungsstudien von 3-D Shock-Control-Bumps mittels numerischer Optimierung (Design of 3D shock control bumps by numerical optimisation, PhD Thesis, Institute for Aerodynamics and Gas Dynamics, University of Stuttgart, 2009.
König, B., Numerical and experimental validation of three-dimensional shock control bumps, AIAA Paper 2008-4001, 4th AIAA Flow Control Conference, Seattle, Washington, 2008.
Ogawa, H. and Babinsky, H., Wind-tunnel set up for investigations of normal shock wave/boundary layer interaction control, AIAA J., vol 44, pp 2803–2805, 2006.
Ogawa, H., Experimental and analytical investigation of transonic shock/boundary layer interaction control with three-dimensional bumps, PhD Thesis, University of Cambridge, 2006.
Menter F., Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications, AIAA Journal, 32:1598–1605, 1994
Kroll, N., and Fassbender, J. K., MEGAFLOW - Numerical Flow Simulation for Aircraft Design, Springer Verlag Berlin/Heidelberg/New York, ISBN 3-540-24383-6.
Streit, T., Horstmann, K.-H., Schrauf, G., Hein, S., Fey, U., Egami, Y., Perraud, J., El Din, I., Cella, U., Quest, J.: Complementary Numerical and Experimental Data Analysis of the ETW Telfona Pathfinder Wing Transition Tests, 49th AIAA Aerospace Sciences Meeting, AIAA 2011-881.
Sun, C-C. and Childs, M.E., A modified wall wake velocity profile for turbulent compressible boundary layers, J. Aircraft vol 10, pp. 381–383, 1973.
Drela, M. and Giles, M.B., Viscous-Inviscid Analysis of Transonic and Low Reynolds Number Airfoils, AIAA Journal, Vol. 25, No. 10, pp. 1347–1355, 1987.
Nübler, K., Colliss, S., Lutz, T., Krämer, E., Babinsky, H., Shock Control Bump Robustness Enhancement, 50th AIAA Aerospace Sciences Meeting Nashville, Tennessee, AIAA 2012–0046, 2012.
Bruce, P.J.K. and Babinsky, H., An experimental investigation of the flow physics of three-dimensional shock control bumps, 49th AIAA Aerospace Sciences Meeting, Orlando, Florida, AIAA 2011–855, 2011.
Wong, W.S., Qin, N., Sellars, N., Holden, H., Babinsky, H., A combined experimental and numerical study of flow structures over three-dimensional shock control bumps, Aerospace Science and Technology, 12, pp. 436–447, 2008.
Eastwood, J.P. and Jarrett, J.P., Towards designing with 3D bumps for wing drag reduction, 49th AIAA Aerospace Sciences Meeting, Orlando, Florida, AIAA 2011–1168, 2011.
Colliss, S.P., Babinsky, H., Bruce, P.J.K., Nübler, K. and Lutz, T., An experimental investigation of three-dimensional shock control bumps applied to transonic airfoils, 50th AIAA Aerospace Sciences Meeting, Nashville, Tennessee, AIAA 2012–43, 2012.
Perry, A.E. and Hornung, H., Some aspects of three-dimensional separation, part II: Vortex Skeletons, Z. Flugwiss. Weltraum., vol. 8, pp 155–160, 1984.
Ashill, P.R., Fulker, J.L. and Hackett, K.C., A review of recent developments in flow control, The Aeronautical Journal, vol 109, no 1, pp 205–232, 2005.
Acknowledgements
The research leading to these results has received funding from the European Union Seventh Framework Programme (FP7/2007–2013) under grant agreement number 271843 as part of the NextWing project, a component of the Smart Fixed Wing Aircraft initiative.
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Nübler, K., Colliss, S.P., Lutz, T., Babinsky, H., Krämer, E. (2013). Numerical and Experimental Examination of Shock Control Bump Flow Physics. In: Nagel, W., Kröner, D., Resch, M. (eds) High Performance Computing in Science and Engineering ‘12. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-33374-3_25
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DOI: https://doi.org/10.1007/978-3-642-33374-3_25
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