I need some help from you aerodynamic masters. I am doing a small project for my controls lab course. We get to choose anything we want, and so I decided to make a pitch rate loop for an autopilot. The setup is very basic, I am going to carve a wing out of Styrofoam and attach a servo to a control surface. The wing will have a rod going through the COM that is attached w roller bearings to a stand. So the wing is fixed to the stand and can pivot clockwise/counter clockwise around the COM. The idea is to get a house fan to provide airflow and have Simulink move the servo so that it always keeps the wing level. The angle will be measured either with an encoder or a potentiometer. Once we get that working we can then suspend masses at various points along the airfoil to change the location of the CG. This will cause the wing to pivot forward or aft around the shaft passing through the original COM. Then the control loop can correct this error out by command up or down elevator until the wing remains level once again. We need to show some simple calculations that this idea is feasible. Since the wing is rigidly attached to the stand, the airflow only has to be sufficient to allow for rotations. So, what equations would be helpful here? Also, if you know how the control loops should look like, that would be nice to see as well. I am not a fluids person.......so my guess would be that the force generated on the elevator would be proportional to the velocity, area and density. I want to make a simple, standard airfoil (Clark Y maybe?). The wing will be small, about 9" x 12" max. Thanks for your ideas.