<FASTOAD_model>
  <data>
    <TLAR>
      <NPAX_design>2.0<!--design number of passengers (two pilots are included de facto, meaning for a 2 seater, NPAX_design is equal to 0)--></NPAX_design>
      <luggage_mass_design units="kg">70.0<!--luggage design mass--></luggage_mass_design>
      <range units="NM">800.0<!--top-level requirement: design range--></range>
      <v_approach units="kn">78.0<!--approach speed--></v_approach>
      <v_cruise units="kn">160.0<!--cruise speed--></v_cruise>
      <v_max_sl units="kn">171.0<!--maximum speed at sea level--></v_max_sl>
    </TLAR>
    <geometry>
      <flap_type>1.0<!--flap type (0.0 - plain flap, 2.0 - single slotted flap, 3.0 - split flap)--></flap_type>
      <has_T_tail>1.0<!--0=horizontal tail is attached to fuselage / 1=horizontal tail is attached to top of vertical tail--></has_T_tail>
      <cabin>
        <aisle_width units="m">0.0<!--width of aisles--></aisle_width>
        <luggage>
          <mass_max units="kg">90.0<!--maximum luggage mass--></mass_max>
        </luggage>
        <seats>
          <passenger>
            <NPAX_max>2.0<!--maximum number of passengers in the aircraft--></NPAX_max>
            <count_by_row>2.0<!--number of passenger seats per row--></count_by_row>
            <length units="m">0.8<!--passenger seats length--></length>
            <width units="m">0.565<!--width of passenger seats--></width>
          </passenger>
          <pilot>
            <length units="m">0.7<!--pilot seats length--></length>
            <width units="m">0.565<!--width of pilot seats--></width>
          </pilot>
        </seats>
      </cabin>
      <flap>
        <chord_ratio>0.1<!--mean value of (flap chord)/(section chord)--></chord_ratio>
        <span_ratio>0.65<!--ratio (width of flaps)/(total span)--></span_ratio>
      </flap>
      <fuselage>
        <rear_length units="m">4.0<!--length of rear non-cylindrical part of the fuselage--></rear_length>
      </fuselage>
      <horizontal_tail>
        <area units="m**2">3.44<!--horizontal tail area--></area>
        <aspect_ratio is_input="False">3.84<!--aspect ratio of horizontal tail--></aspect_ratio>
        <elevator_chord_ratio is_input="True">0.3<!--elevator chord ratio--></elevator_chord_ratio>
        <sweep_25 units="deg">4.0<!--sweep angle at 25% chord of horizontal tail--></sweep_25>
        <taper_ratio>1.0<!--taper ratio of horizontal tail--></taper_ratio>
        <thickness_ratio>0.125<!--thickness ratio of horizontal tail--></thickness_ratio>
        <MAC>
          <at25percent>
            <x>
              <from_wingMAC25 units="m">4.8<!--distance along X between 25% MAC of wing and 25% MAC of horizontal tail--></from_wingMAC25>
            </x>
          </at25percent>
        </MAC>
      </horizontal_tail>
      <landing_gear>
        <type>1.0<!--0=non-retractable / 1=retractable--></type>
      </landing_gear>
      <propeller>
        <average_rpm units="rpm">2500.0</average_rpm>
        <blades_number>2.0<!--number of blades on the propeller--></blades_number>
        <chord_vect units="m">[0.11163526, 0.15856474, 0.16254664, 0.21189369, 0.18558474, 0.11163526, 0.11163526]<!--blade chord at the station along the radius stored in radius_ratio_vect--></chord_vect>
        <depth units="m">0.3<!--depth of the propeller--></depth>
        <diameter units="m">1.93<!--propeller diameter--></diameter>
        <hub_diameter units="m">0.4<!--propeller hub diameter--></hub_diameter>
        <radius_ratio_vect>[0.165, 0.3, 0.45, 0.655, 0.835, 0.975, 1.0]<!--blade station at which blade geometric properties are sampled, as a percent of blade radius--></radius_ratio_vect>
        <sweep_vect units="deg">[0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0]<!--blade sweep at the station along the radius stored in radius_ratio_vect--></sweep_vect>
        <twist_vect units="deg">[59.9549991, 54.62741602, 50.40984436, 46.40324949, 43.92011437, 42.42629402, 42.19068494]<!--blade twist at the station along the radius stored in radius_ratio_vect--></twist_vect>
      </propeller>
      <vertical_tail>
        <area units="m**2">2.653<!--vertical tail area--></area>
        <aspect_ratio>1.2<!--aspect ratio of vertical tail--></aspect_ratio>
        <sweep_25 units="deg">30.0<!--sweep angle at 25% chord of vertical tail--></sweep_25>
        <taper_ratio>0.62<!--taper ratio of vertical tail--></taper_ratio>
        <thickness_ratio>0.125<!--thickness ratio of vertical tail--></thickness_ratio>
        <rudder>
          <chord_ratio>0.4<!--flap rudder as a percentage of the wing chord--></chord_ratio>
          <max_deflection units="deg">30.0<!--rudder maximum deflection--></max_deflection>
        </rudder>
      </vertical_tail>
      <wing>
        <area units="m**2">16.638<!--wing reference area--></area>
        <aspect_ratio>7.981<!--wing aspect ratio--></aspect_ratio>
        <sweep_25 units="deg">0.0<!--sweep angle at 25% chord of wing--></sweep_25>
        <taper_ratio>1.0<!--taper ratio of wing--></taper_ratio>
        <thickness_ratio>0.15<!--mean thickness ratio of wing--></thickness_ratio>
        <aileron>
          <chord_ratio is_input="True">0.26<!--aileron chord as a percentage of the wing chord--></chord_ratio>
          <max_deflection units="rad" is_input="True">40.0</max_deflection>
          <span_ratio is_input="True">0.32</span_ratio>
        </aileron>
        <kink>
          <span_ratio>0.0<!--ratio (Y-position of kink)/(semi-span)--></span_ratio>
        </kink>
        <MAC>
          <at25percent>
            <x units="m">2.638<!--X-position of the 25% of mean aerodynamic chord of wing w.r.t. aircraft nose (drives position of wing along fuselage)--></x>
          </at25percent>
        </MAC>
      </wing>
      <propulsion>
        <engine>
          <count>2.0<!--number of engines--></count>
          <layout>1.0<!--position of engines (1=under the wing / 2=rear fuselage / 3=nose)--></layout>
          <y_ratio>0.34<!--engine position with respect to total span--></y_ratio>
        </engine>
      </propulsion>
    </geometry>
    <propulsion>
      <fuel_type>1.0<!--engine fuel type (1.0 - gasoline, 2.0 - gasoil)--></fuel_type>
      <max_rpm units="min**-1">2700.0<!--maximum number of rotation per minute on the engine--></max_rpm>
      <IC_engine>
        <max_power units="W">130000.0<!--maximum power of the engine--></max_power>
        <strokes_nb>4.0<!--number of strokes on the engine--></strokes_nb>
      </IC_engine>
    </propulsion>
    <handling_qualities>
      <static_margin>
        <target>0.25<!--static margin we want to achieve--></target>
      </static_margin>
    </handling_qualities>
    <mission>
      <sizing>
        <fuel units="kg">0.0<!--consumed fuel mass during whole mission--></fuel>
        <landing>
          <elevator_angle units="deg">-20.0<!--position of the elevator during landing--></elevator_angle>
          <target_sideslip units="deg">12.0</target_sideslip>
        </landing>
        <takeoff>
          <elevator_angle units="deg">-20.0<!--position of the elevator during takeoff--></elevator_angle>
          <flap_angle units="deg">10.0<!--flap angle during takeoff phase in sizing mission--></flap_angle>
          <friction_coefficient_no_brake>0.03<!--ground friction coefficient with no brake in sizing mission--></friction_coefficient_no_brake>
          <thrust_rate>1.0<!--thrust rate during takeoff phase--></thrust_rate>
        </takeoff>
        <taxi_in>
          <duration units="s">300.0<!--duration of taxi-in phase in sizing mission--></duration>
          <speed units="kn">20.0<!--speed during taxi-in phase in sizing mission--></speed>
          <thrust_rate>0.3<!--thrust rate (between 0.0 and 1.0) during taxi-in phase in sizing mission--></thrust_rate>
        </taxi_in>
        <taxi_out>
          <duration units="s">300.0<!--duration of taxi-out phase in sizing mission--></duration>
          <speed units="kn">20.0<!--speed during taxi-out phase in sizing mission--></speed>
          <thrust_rate>0.3<!--thrust rate (between 0.0 and 1.0) during taxi-out phase in sizing mission--></thrust_rate>
        </taxi_out>
        <cs23>
          <characteristic_speed>
            <vd units="kn">194.0<!--limit speed--></vd>
          </characteristic_speed>
          <sizing_factor>
            <ultimate_aircraft>5.7<!--ultimate load factor that the aircraft will experience (default value is 5.7)--></ultimate_aircraft>
          </sizing_factor>
        </cs23>
        <main_route>
          <cruise>
            <altitude units="ft">8000.0<!--altitude during cruise phase in sizing mission--></altitude>
          </cruise>
          <descent>
            <descent_rate units="ft/min">-300.0<!--target descent rate for the aircraft--></descent_rate>
          </descent>
          <reserve>
            <duration units="min">45.0<!--duration of the reserve segment--></duration>
          </reserve>
          <climb>
            <climb_rate>
              <cruise_level units="ft/min">700.0<!--target climb rate at the end of climb--></cruise_level>
              <sea_level units="ft/min">1200.0<!--target climb rate at sea level--></sea_level>
            </climb_rate>
          </climb>
        </main_route>
      </sizing>
    </mission>
    <weight>
      <airframe>
        <fuselage>
          <k_factor>1.0<!--proportional corrective factor for fuselage mass--></k_factor>
        </fuselage>
        <horizontal_tail>
          <k_factor>1.0<!--proportional corrective factor for horizontal tail mass--></k_factor>
        </horizontal_tail>
        <vertical_tail>
          <k_factor>1.0<!--proportional corrective factor for vertical tail mass--></k_factor>
        </vertical_tail>
        <wing>
          <k_factor>1.0<!--proportional corrective factor for wing mass--></k_factor>
        </wing>
      </airframe>
    </weight>
  </data>
  <settings>
    <propulsion>
      <IC_engine>
        <k_factor_sfc>1.1</k_factor_sfc>
      </IC_engine>
    </propulsion>
    <weight>
      <aircraft>
        <CG>
          <range>0.187<!--distance between front position and aft position of CG, as ratio of mean aerodynamic chord (allows to have front position of CG, as currently, FAST-OAD estimates only the aft position of CG)--></range>
        </CG>
      </aircraft>
      <airframe>
        <landing_gear>
          <front>
            <weight_ratio>0.23<!--part of aircraft weight that is supported by front landing gear--></weight_ratio>
          </front>
        </landing_gear>
      </airframe>
    </weight>
  </settings>
</FASTOAD_model>
