Cooperation of Trailing-Edge Flap and Shock Control Bump for Robust Buffet Control and Drag Reduction

At transonic flight conditions, the buffet caused by interaction between shock waves and boundary layers can degrade an aircraft’s aerodynamic performance even threaten its safety. In this paper, control bumps, originally designed to reduce wave drag at cruise speeds, are applied enhance robustness of closed-loop system using trailing-edge flap. For OAT15A supercritical airfoil, a is first with feedback signal lift coefficient. Then, bumps for reduction integrated into active system. The results show that flap be greatly enhanced coupling bumps. steady state under control, slightly increase airfoil lift–drag ratio. More importantly, ranges parameters effectively suppress significantly enlarged help bumps; thus, enhanced.