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I've checked the lift requirements of the aircraft and selected an optimal airfoil and designed a wing with dimensions of MAC 47cm and semi-span of 163.2 cm and a airfoil S1223. The horizontal stabilizer has a MAC of 17.5cm and semi span of 50cm with NACA 0012.

How can I calculate the change in Cl of the elevator with respect to the angle of deflection of the elevator?

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