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')