The lift equation states that lift L is equal to the lift coefficient Cl times the density r times half of the velocity V squared times the wing area A. L = Cl * A * .5 * r * V^2. For given air conditions, shape, and inclination of the object, we have to determine a value for Cl to determine the lift.
Use the law of sines 11/sin50°=13/sinθ 11/0.766=13/sinθ 11sinθ=13(0.766) 11sinθ=9.958 sinθ=9.958/11 sinθ=0.9052727 use arcsin on your calculator θ=64.86°
