//Example 11-5 Lift and Drag of commercial Airplane
m = 70000 //mass of commercial airplane [kg]
A = 150 //wing planeform area [m^2]
V = 558 //crusing speed of the plane [km/hr]
rho_altitude = 0.312 //density of air at altitude of 12000m [kg/m^3]
rho_ground = 1.2 //density of air on ground [kg/m^3]
C_Lmax_flap = 3.48 //maximum lift coefficient with flaps
C_Lmax = 1.52 //maximum lift coefficient without flaps
g = 9.81 //gravitational acceleration [m/s^2]