def main():
# new units style
a = 4 * Units.mm # convert into base units
b = a / Units.mm # convert out of base units
engine = Data()
wing = Data()
aircraft = Data()
fuselage = Data()
horizontal = Data()
vertical = Data()
# Parameters Required
aircraft.Nult = 1.5 * 2.5 # Ultimate load
aircraft.TOW = 52300. * Units.kilograms # Maximum takeoff weight in kilograms
aircraft.zfw = 42600. * Units.kilograms # Maximum zero fuel weight in kilograms
aircraft.Nlim = 2.5 # Limit Load
aircraft.num_eng = 2. # Number of engines on the aircraft
aircraft.num_pax = 110. # Number of passengers
aircraft.wt_cargo = 0. * Units.kilogram # Mass of cargo
aircraft.num_seats = 110. # Number of seats on aircraft
aircraft.ctrl = "partially powered" # Specify fully powered, partially powered or anything else is fully aerodynamic
aircraft.ac = "medium-range" # Specify what type of aircraft you have
aircraft.w2h = 16. * Units.meters # Length from the mean aerodynamic center of wing to mean aerodynamic center of the horizontal tail
wing.gross_area = 92. * Units.meter**2 # Wing gross area in square meters
wing.span = 27.8 * Units.meter # Span in meters
wing.taper = 0.28 # Taper ratio
wing.t_c = 0.105 # Thickness-to-chord ratio
wing.sweep = 23.5 * Units.deg # sweep angle in degrees
wing.c_r = 5.4 * Units.meter # Wing exposed root chord length
wing.mac = 12. * Units.ft # Length of the mean aerodynamic chord of the wing
fuselage.area = 320. * Units.meter**2 # Fuselage wetted area
fuselage.diff_p = 8.5 * Units.force_pound / Units.inches**2 # Maximum differential pressure
fuselage.width = 3. * Units.meter # Width of the fuselage
fuselage.height = 3.35 * Units.meter # Height of the fuselage
fuselage.length = 36.24 * Units.meter # Length of the fuselage
engine.thrust_sls = 18500. * Units.force_pound # Define Thrust in Newtons
horizontal.area = 26. * Units.meters**2 # Area of the horizontal tail
horizontal.span = 12.08 * Units.meters # Span of the horizontal tail
horizontal.sweep = 34.5 * Units.deg # Sweep of the horizontal tail
horizontal.mac = 2.4 * Units.meters # Length of the mean aerodynamic chord of the horizontal tail
horizontal.t_c = 0.11 # Thickness-to-chord ratio of the horizontal tail
horizontal.exposed = 0.9 # Fraction of horizontal tail area exposed
vertical.area = 16. * Units.meters**2 # Area of the vertical tail
vertical.span = 5.3 * Units.meters # Span of the vertical tail
vertical.t_c = 0.12 # Thickness-to-chord ratio of the vertical tail
vertical.sweep = 35. * Units.deg # Sweep of the vertical tail
vertical.t_tail = "no" # Set to "yes" for a T-tail
aircraft.weight = Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical)
outputWeight(aircraft,'weight_EMB190.dat')
