Numerical Optimization of Finite Shock Control Bumps

Abstract

Shock control is an important mean to further increase the aerodynamic efficiency of transport aircraft. One promising approach to reduce the strength of occuring shock waves is the shock control bump. In the current paper a straight forward approach to the application of shock control bumps to swept wings is presented. Finite span shock control bumps are mounted on an infinite span wing. Directly applied 2d–optimized shock control bumps are analysed for the unswept and swept wing. Spanwise finite shock control bumps are designed for the swept wing using direct numerical optimization. It is shown that in the unswept flow case the efficiency of finite shock control bumps is better than on swept wings. In oblique flow, finite span shock control bumps suffer increasing losses in efficiency with decreasing spanwise extension. Some improvements may be achieved by a more detailed design of the spanwise flanks of finite bumps.