Design, Multi-element Airfoil Optimization Method Based On The Conjugate Equation

Aerodynamic optimization design of airfoils and wings using control theory approach can avoid the great computation time cost in the traditional approach when lots of design variables are required to solve the gradients. The control theory method only needs double time of the fluid field computation to obtain the global gradients, through solving the adjoint equations of the governing equations. It can provide enough accuracy in design optimization as well. The adjoint method can be used broadly in design optimization such as drag minimization at the designed lift conditions.In this paper based on the optimization design method using control theory for airfoils, a design method for multi-element airfoils is developed with the chimera grids. And optimization computation for reducing drag of Shockwave of single airfoil in transonic flow is also successful. All the jobs are conducted without the consideration of viscosity.