def execute(self):
        wing = Wing(flap_type='single_slot',
            configuration='landing',
            slats=True,
            k_aero=self.k_aero,
            sweep=self.sweep,
            flap_span=[0.2, 0.4],
            taper_ratio=self.taper_ratio)

        self.aircraft = Aircraft(wing=wing,
                                 stores=[Payload('Crew', weight=200),
                                         Payload('Cannon', weight=270),
                                         Payload('Ammunition Feed System', weight=405),
                                         Payload('Ammunition', weight=550),
                                         Payload('Casings', weight=198),
                                         Payload('AMRAAMs', weight=332, quantity=4, cd_r=0.005, expendable=True),
                                         Payload('AIM-9Xs', weight=188, quantity=2, cd_r=0.002, expendable=True)],
                                 drag_chute=None)#{'diameter': 15.6, 'cd': 1.4})

        mission = Mission(segments=[Segment('warmup',
                                            altitude=self.airfield_altitude,
                                            speed=0,
                                            time=60),
                                    Segment('takeoff',
                                            altitude=self.airfield_altitude,
                                            speed=150,
                                            field_length=self.tofl,
                                            temperature=100),
                                    Segment('climb',
                                            altitude=self.airfield_altitude,
                                            speed=500),
                                    Segment('cruise',
                                            altitude=self.cruise_altitude,
                                            speed=self.cruise_speed,
                                            range=self.cruise_range,
                                            release=[()]),
                                    Segment('descend',
                                            altitude=self.dash_altitude,
                                            speed=1000),
                                    Segment('dash',
                                            altitude=self.dash_altitude,
                                            speed=self.dash_speed,
                                            range=self.dash_range),
                                    Segment('climb',
                                            altitude=self.cruise_altitude,
                                            speed=1000),
                                    Segment('cruise',
                                            altitude=self.cruise_altitude,
                                            speed=1050,
                                            range=self.cruise_range),
                                    Segment('descend',
                                            altitude=self.airfield_altitude,
                                            speed=1000),
                                    Segment('land',
                                            altitude=self.airfield_altitude,
                                            speed=self.landing_speed,
                                            field_length=self.ldgfl)])

        self.aircraft._synthesize(mission)
        self.aircraft._size(mission)

        self.togw = self.aircraft.w_to
        self.wing_area = self.aircraft.wing.area
        self.thrust = self.aircraft.engine.max_thrust * self.aircraft.num_engines

        cost = Cost(aircraft=aircraft,
                    stealth=self.stealth,
                    avionics_complexity=self.avionics_complexity,
                    materials_complexity=self.materials_complexity,
                    avionics_weight=self.avionics_weight_fraction,
                    quantity=self.quantity,
                    year=self.cost_year)

        self.acq_cost = cost.estimate_acquisition() / 1e6
class Fighter(Component):

    k_aero = Float(0.5, iotype='in', low=0, high=1, desc="K-Factor for aerodynamic efficiency, higher is better")
    taper_ratio = Float(0.2, iotype='in', low=0, high=1, desc="The wing tip chord divided by the wing root chord")
    sweep = Float(30, iotype='in', low=0, high=55, units='deg', desc="Angle between wing's quarter-chord line and a line perpendicular to the free-stream")

    tofl = Float(1500, iotype='in', low=0, units='ft', desc="Takeoff Field Length")
    airfield_altitude = Float(0, iotype='in', low=0, units='ft', desc="Altitude at which the airfield is at")

    cruise_altitude = Float(30000, iotype='in', low=1000, units='ft', desc="Altitude at which the aircraft is will cruise")
    cruise_speed = Float(700, iotype='in', low=0, units='knot', desc="Speed at which the aircraft will cruise")
    cruise_range = Float(150, iotype='in', low=0, units='nmi', desc="Distance the aircraft will cover in each cruise segment")

    dash_altitude = Float(30000, iotype='in', low=1000, units='ft', desc="Altitude at which the aircraft is will perform the dash segment")
    dash_speed = Float(1492, iotype='in', low=0, units='knot', desc="Speed at which the aircraft will dash")
    dash_range = Float(100, iotype='in', low=0, units='nmi', desc="Distance the aircraft will cover in each dash segment")

    ldgfl = Float(1500, iotype='in', low=0, units='ft', desc="Landing Field Length")
    landing_speed = Float(150, iotype='in', low=0, units='knot', desc="Speed the aircraft will fly when touching down")

    togw = Float(iotype='out', units='lbm', desc="Take-off Gross Weight")
    wing_area = Float(iotype='out', units='ft**2', desc="Wing Area")
    thrust = Float(iotype='out', units='lbf', desc="Maximum Thrust produced by the engines")

    quantity = Int(iotype='in', low=0, desc="Number of aircraft to manufacture")
    stealth = Float(iotype='in', low=0, high=1, desc="Degree of stealthiness required")
    materials_complexity = Float(iotype='in', low=0, high=1, desc="Degree of difficulty with working with selected materials")
    avionics_weight_fraction = Float(iotype='in', low=0, high=1, desc="Amount of avionics from a nominal amount")
    avionics_complexity = Float(iotype='in', low=0, high=1, desc="Degree of complexity of the avionics in the aircraft")
    cost_year = Int(iotype='in', low=1999, desc="Year dollars for which to calculate the cost of the aircraft")

    acq_cost = Float(iotype='out', units='MUSD', desc="Estimated acquisition cost (fly away cost) for the program")

    def execute(self):
        wing = Wing(flap_type='single_slot',
            configuration='landing',
            slats=True,
            k_aero=self.k_aero,
            sweep=self.sweep,
            flap_span=[0.2, 0.4],
            taper_ratio=self.taper_ratio)

        self.aircraft = Aircraft(wing=wing,
                                 stores=[Payload('Crew', weight=200),
                                         Payload('Cannon', weight=270),
                                         Payload('Ammunition Feed System', weight=405),
                                         Payload('Ammunition', weight=550),
                                         Payload('Casings', weight=198),
                                         Payload('AMRAAMs', weight=332, quantity=4, cd_r=0.005, expendable=True),
                                         Payload('AIM-9Xs', weight=188, quantity=2, cd_r=0.002, expendable=True)],
                                 drag_chute=None)#{'diameter': 15.6, 'cd': 1.4})

        mission = Mission(segments=[Segment('warmup',
                                            altitude=self.airfield_altitude,
                                            speed=0,
                                            time=60),
                                    Segment('takeoff',
                                            altitude=self.airfield_altitude,
                                            speed=150,
                                            field_length=self.tofl,
                                            temperature=100),
                                    Segment('climb',
                                            altitude=self.airfield_altitude,
                                            speed=500),
                                    Segment('cruise',
                                            altitude=self.cruise_altitude,
                                            speed=self.cruise_speed,
                                            range=self.cruise_range,
                                            release=[()]),
                                    Segment('descend',
                                            altitude=self.dash_altitude,
                                            speed=1000),
                                    Segment('dash',
                                            altitude=self.dash_altitude,
                                            speed=self.dash_speed,
                                            range=self.dash_range),
                                    Segment('climb',
                                            altitude=self.cruise_altitude,
                                            speed=1000),
                                    Segment('cruise',
                                            altitude=self.cruise_altitude,
                                            speed=1050,
                                            range=self.cruise_range),
                                    Segment('descend',
                                            altitude=self.airfield_altitude,
                                            speed=1000),
                                    Segment('land',
                                            altitude=self.airfield_altitude,
                                            speed=self.landing_speed,
                                            field_length=self.ldgfl)])

        self.aircraft._synthesize(mission)
        self.aircraft._size(mission)

        self.togw = self.aircraft.w_to
        self.wing_area = self.aircraft.wing.area
        self.thrust = self.aircraft.engine.max_thrust * self.aircraft.num_engines

        cost = Cost(aircraft=aircraft,
                    stealth=self.stealth,
                    avionics_complexity=self.avionics_complexity,
                    materials_complexity=self.materials_complexity,
                    avionics_weight=self.avionics_weight_fraction,
                    quantity=self.quantity,
                    year=self.cost_year)

        self.acq_cost = cost.estimate_acquisition() / 1e6