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+//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] \ No newline at end of file