Numerical and Experimental Validation of Three-Dimensional Shock Control Bumps
B. König, M. Pätzold, Th. Lutz, E. Krämer, H. Rosemann, K. Richter and H. Uhlemann
Journal of Aircraft, Vol. 46, No. 2, S. 675-682, 2009.
Numerical and experimental studies have been performed to show the potential for drag reductions of an array of discrete three-dimensional shock control bumps. The bump contour investigated was specifically designed by means of CFD-based numerical optimization for wind tunnel testing on a modern transonic airfoil. The experimental investigations focused on turbulent flow at a Reynolds number of 5 million and were carried out at the Transonic Wind Tunnel Göttingen. Drag reductions of around 10% in the drag-rise region were found in the experiment even though the results were influenced by wind tunnel interference effects. A detailed numerical study of the wind tunnel environment reproduced the influence of the wind tunnel walls on the bump performance and gave good agreement to the experimental results.