Adaptive Shock Control Bumps

This paper describes a numerical investigation into the optimal design of adaptive shock control bumps (SCB) for transonic wings. A multi-disciplinary approach to optimization is utilized, combining structural and aerodynamic analysis to ensure that optimal adaptive SCB do not exceed material constraints whilst maintaining aerodynamic qualities. It is found that adaptive SCB can perform to within 95% of the non-structurally constrained bumps but over a much wider flight envelope. Two dimensional single crest bumps have been shown to match the performance of table top bumps originating from three dimensional SCB. Total pressure recovery has been successfully used as a performance metric and will provide valuable comparisons to wind tunnel experiments with a prototype adaptive SCB.