for straight and level flight. Since CL is proportional to angle of attack ( ), then for an uncambered wing and a 2% increase in produces a 2% increase in and a 2% increase in load factor n.
As proof:- when = 0.35 at = 4.43º
Now increase by 2% to get 4.52º. CL = .079 x 4.52 = 0.357.
Thus lift has increase by 2% and load factor has increased by 2%.
For an example with a cambered wing, where + there is insufficient information to complete this example.