Assume that the lift coefficient for an aircraft wing varies linearly between 0.1 at 0° angle of attack to 0.9 at 8°. At what angle of attack must the wing be for the plane to fly horizontally at 250...

Assume that the lift coefficient for an aircraft wing varies linearly between 0.1 at 0° angle of attack to 0.9 at 8°. At what angle of attack must the wing be for the plane to fly horizontally at 250 km/h at an altitude of 2000 m? The weight is 18 kN and the wing area is 30 m².