Semi-Active Flutter Suppression by Means of Shock-Control-Bumps

Kurzfassung

This thesis investigates the influence of shock control bumps (SCB) on the aerodynamics and transonic flutter behavior under attached flow conditions. It uses unsteady RANS equations to determine the aerodynamic properties. Furthermore, it implements a structural model and determines the linearized flutter solution. The aerodynamic results obtained from the two-dimensional study were successfully transferred to a three-dimensional wing. In both cases, the SCB introduced a shock into a previously shock-free flow field. Furthermore, an improvement of the flutter behavior in the region of the transonic dip was observed with SCBs for both the airfoil and the wing.