Using Shock Control Bump to Weaken the Interaction of Shock and Boundary Layer in Transonic Flight Regime

The most important factors for the sudden increase in drag coefficient in transonic flight regime are the occurrence of shock waves and its interaction with boundary layer. Using shock control bump to weaken the interaction of shock and boundary layer makes it possible to experience lower drag coefficient in a range of off-design Mach numbers. In this study, a differential evolution algorithm is used to find the optimum shape and location of shock control bump respect to free stream condition. This study clearly shows that the effectiveness of this method in improving the aerodynamic performance and reducing drag is totally a function of flight condition; The method is effective in fairly wide range of off-design Mach numbers; However, boundary layer separation and oscillatory shock wave in downstream of bump region is the main limitation of this method for the case of strong shock waves.