Use the lift equation: L = CL * (1/2 pv²) * Area
A sailplane has 20 m² of wing area. If tilted up to its highest angle of attack, its lift coefficient CL
= 1.2. The density of air at sea level is 1.2 kg/m³. How much lift (in Newtons, N) can it generate
when it takes off at a speed of 50 m/s?