An airfoil of surface area 1ft squared is tested for lift (L) in a wind tunnel. At an angle of attack of 5 degrees with standard air of density 0.0024 slugs/ft cube at a speed of 100 ft/sec, the lift is measured as 7.0 pounds. Was is the lift coefficient Cl?
For a prototype wing area 100 ft squared, what is the lift Lp at an air speed of 100 mph at the same angel of attack of 5 degrees.
Please show work and formulas