Investigations on Shock Control Bumps for Infinite Swept Wings
M. Kutzbach, Th. Lutz and S. Wagner
2nd AIAA Flow Control Conference, Portland, Oregon, USA, June 28 - July 1, 2004
In the context of adaptive wings for future transport aircraft the potential of a shock control bump for reducing wave drag is investigated using a direct numerical optimization approach. Evaluation of the designs is accomplished by a RANS and a coupled Euler-boundary-layer code. Firstly, the different analysis tools are compared for two-dimensional airfoil flows. Thereafter, the method is applied to the optimization of shock control bumps for infinite swept wings. It is shown that within the accuracy of the turbulence models considered, neither the optimum shock bump contour, nor its efficiency is significantly influenced by oblique flow. This could not be excluded a priori due to the mixing character of inherently three-dimensional turbulent boundary layers.