I am considering a model wing inside a wind tunnel supported from underneath from its center of mass. Two load cells can be used, when properly oriented, to measure the lift force and the drag force. How can two load cells be arranged to also measure the pitching moment and specifically the constant aerodynamic moment I discussed in other threads?
Thank you!
I had imagined simply mounting your lift and drag sensors on a simple (HO gauge model railroad) track for a DIY homebuilt wind tunnel.
Pitching moments for your wing could be done as a separate experiment. Your could pivot on your aerodynamic center (as an axle) and measure pitching torque moments with the load cell attached to the end of the fuselage. Once these moments are established, you can then design the H stab based on area and distance from your wing. Ideally, the H stab will keep your pitching moments zero through all angles of attack (including stall), leaving pitch control to the pilot (with the elevator).
Similar study can be done with you center of pressure (center of all lifts), once you establish it in your planform design.
