I would like to create a simple forces diagram (like a sketch). The lift produced by the wing depends upon to the distance from the the longitudinal axis, but, in order to make it easier, I’m taking the lift as a constant in the whole wing. Here is the question, I need to calculate the moment produced by the wing taking only the drag and lift forces by the wings, what distance should I take?
Although I think the answer will be a percentage of the wingspan, here is some data if needed.
- Wingspan: 1m
- AR: 11
- Wing configuration: tapered
- Root chord: 0.17m
- Tío chord: 0.12m
Since I have the drag and lift forces and Cp, I need to calculate the distance from the x axis to this force application points. How can I estimate those distances?