In airfoils, the aerodynamic center is usually found close to the quarter chord point, but for quick calculations, we assume it lies on the quarter chord.
What I am looking for, is if there is any way to find a rough estimate as to where the aerodynamic center is actually located on a tested airfoil - given only lift and drag data.
The tested airfoil is mounted on athe sting on its quarter-chord point, which sits on top of a force transducer. The angle of attack is varied throughout the test.