Numerical analysis of shock characteristics control based on bump

Abstract

The effects of bump control on shock aerodynamic characteristics have been investigated by simulations. A bump control that based on the changes of local upper surface of two-dimensional (2D) airfoil or three-dimensional (3D) wing model has been applied to affect the shock intensity and position. The simulation results are close of other experiment when the calculate parameters are same with each other. The simulations show that the drag and lift characteristics can be improved with the bump control, and the results of improvement strongly depend on control parameters. For the 2D RAE2822 airfoil, the optimal control position of the bump control must keep close to the position of the shock wave. The 3D local bump that located on 80% wing span wise and closed to the tip can acquire a batter control results for the 3D RAE2822 wing model.