A group of students and I are designing a theoretical closed-wing drone and need to calculate lift based on the NASA lift equation. We've designed fixed-wing aircraft before and when it came to finding the co-efficient of lift for the airfoil, we just used the NACA charts. Since the aircraft will be closed wing this time around, we are not entirely sure how to go about this. We are very amateur, so I know we are likely missing very obvious things. Thank you for any help that can be provided.