Aerodynamic optimization design of wing-body-nacelle-pylon configuration

A moving grid methodology based on transfinite interpolation (TFI) and radial basis function was adopted for complex configuration. For the problem that may lead to negative jacobian near configuration surface or decline of grid quality, a technology was proposed to remedy the flaw of TFI method: a radial basis function methodology was utilized to achieve the displacements of edges not directly linked to the configuration surface grid, and a linear interpolation was introduced to get the displacements of edges directly linked to the configuration surface grid. An efficient configuration surface grid movement method was introduced via TFI method in case of variation of junction lines. By use of descrete adjoint method to compute the gradient of objective function, wing and nacelle of DLR-F6 wing-body-nacelle-pylon configuration was parameterized and optimized. Tests show that 0.000 1 of drag coefficient decline can be gained through optimization considering nacelle's position compared with optimization without considering nacelle's position. Totally, a decrease of 0.001 53 aerodynamic drag coefficient can be obtained through optimization.