Unsteady aerodynamic sensitivities towards shape design variables are critical for multidisciplinary design optimization of aircraft. Sensitivity analysis using finite difference method (FDM) is not reliable due to its reliance on the step size choice. Automatic differentiation using complex variable and dual number has been enabled to a CFD-based aerodynamic solver, ZEUS. Both methods can compute the sensitivities accurately and efficiently. However, the complex variable method (CVD) requires an extreme small number be used as the perturbation to the design variable, which may slow down the computation due to floating number underflow issue. By any rate, CVD is still an approximate method, While the dual number approach theoretically gives exact sensitivity solutions. Numerical example cases on the AGARD wing configurations with the swept angle or the span as the design variable are carried out to demonstrate the validation of the CVD and dual number method implementations.