The answer must be in MatLab

Problem 1 The drag force Fa in a terrestrial aircraft can be calculated with the drag equation: PV2A Fa = Cd 2 Cs is the drag coefficient. Ca = 2.0019 x 107, p is the air density. p = 1 x 10 kg/m', V is the velocity of the aircraft (m/s). A is the reference area. A = 1 m (a) Calculate the drag, if the velocities range from 5 to 50 m/s, with an increment 20 (b) Calculate the power required to overcome the aerodynamic drag. The power is given by: pVA Pa = F, V = Cd 2