Computations of Control Power Using a Preconditioned Continuous Adjoint Method

초록

In this paper, control powers of aircraft control surfaces are computed using a preconditioned continuous adjoint method. To determine of the control derivatives with respect to the control surface deflection, the preconditioned adjoint method with the Weiss and Smith’s preconditioning matrix is developed. The preconditioned adjoint method gives accurate and highly converged adjoint solutions at all Mach numbers. Using the preconditioned adjoint method, the lift and moment control derivatives for an airfoil, a wing, and a blended wing body model are computed and compared with those obtained by a finite difference method.