© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.The automatic differentiation tool, FDOT, is employed to perform sensitivity analyses on an in-house panel code. Sensitivity derivatives obtained are then used for aerodynamic shape optimization of airfoil profiles. A baseline airfoil is optimized with the panel code for the target lift and moment coefficients while minimizing the adverse pressure gradient on the airfoil. Airfoil profiles are parametrized by the Class Shape Transformation. Optimization is performed by a steepest descent algorithm, using a quasi-Newton method. Validation and case studies are presented. It is shown that the aerodynamic loads on the optimized airfoil profile based on the panel code agree well with the RANS solution. In addition, the design optimizations which include minimization of the adverse pressure gradient upstream of the mid-chord reduce the stall angle slightly and achieve mild stall characteristics as expected.