<FDM_CONFIG NAME="c310" VERSION="1.60">
<!--

  File:        c310.xml
  Author:      David Megginson, based on c172.xml by Tony Peden
  CVS Version: $Id: c310.xml,v 1.27 2002/09/24 12:56:05 tony Exp $

  Function: Models a Cessna 310
  Notes:    Try running FlightGear using this command line,
            fgfs -fdm=jsb -aircraft=c310
-->

  <METRICS>
    <!--
    The XYZorigin for measurements is the bottom centre of the
    firewall in front of the rudder pedals; the estimates here take
    the bottom of the airframe directly below the bottom of the
    sloping front windshield, since the 3-views available are external
    only.

    Positive values in the X axis move back towards the tail of the
    plane, positive values in the Y axis move out towards the right
    wing, and positive values in the Z axis move up.

    Wing area (ft^2)
    Wing span (ft)
    Wing avg. chord (ft)
    H. Tail Area (ft^2)
    Wing MAC to H.Tail MAC (ft)
    V. Tail Area (ft^2)
    Wing MAC to V.Tail MAC (ft)
    Ixx (slug-ft^2)
    Iyy (slug-ft^2)
    Izz (slug-ft^2)
    Ixz (slug-ft^2)
    Empty weight (lbs)
    Aerodynamic reference point (close to CG), in aircraft's own
      structural coord system. X, Y, Z, in inches.
    Center of gravity location, empty weight, in aircraft's own
      structural coord system. X, Y, Z, in inches
    Pilot's eyepoint location, in aircraft's own coord system, FROM cg.
     X, Y, Z, in inches
    AC_AERORP   43.2  0.0    59.4
    -->

    AC_WINGAREA   175
    AC_WINGSPAN    36.5
    AC_CHORD        4.9
    AC_HTAILAREA   21.9
    AC_HTAILARM    15.7
    AC_VTAILAREA   16.5
    AC_LV          15.7
    AC_IXX       8884
    AC_IYY       1939
    AC_IZZ      11001
    AC_IXZ          0
    AC_EMPTYWT   3166
    AC_AERORP      46.0   0.0  8.6
    AC_CGLOC       46.0   0.0  8.6
    AC_EYEPTLOC    35.0 -12.0 38.0

  </METRICS>

  <UNDERCARRIAGE>

    <!--
    The gear parameters that can be specified are as follows, IN ORDER OF APPEAANCE:

    AC_GEAR
    <name>                           name of gear entry - no spaces allowed
    <X> <Y> <Z>                      Gear location in aircraft body coords in inches
    <spring constant>                spring constant in lbs/ft
    <damping coefficient>            damping coefficient in lbs/ft/sec
    <dynamic friction coefficient>   Self-explanatory: sliding friction coefficient
    <static friction coefficient>    Self-explanatory: "onset" friction coefficient
    <rolling friction coefficient>   Self-explanatory: rolling friction coefficient
    <steerability attribute>         One of <STEERABLE | FIXED | CASTERED>
    <brake group membership>         One of <LEFT | CENTER | RIGHT | NOSE | TAIL | NONE>
    <max steer angle>                Maximum steerable angle in degrees
    <retractable>                    One of RETRACT or FIXED
    -->


     AC_GEAR    NOSE       -60.2   0.0 -27.0  5400 1600  0.5  0.8 0.02 STEERABLE NONE 20 RETRACT
     AC_GEAR    LEFT_MAIN   50.7 -70.8 -31.0  5400 1600  0.5  0.8 0.02 CASTERED  LEFT  0 RETRACT
     AC_GEAR    RIGHT_MAIN  50.7  70.8 -31.0  5400 1600  0.5  0.8 0.02 CASTERED  RIGHT 0 RETRACT
     AC_GEAR    TAIL_SKID  221.8   0.0   0.0 20000 1000  0.2   0.2 0.2  FIXED NONE 0 FIXED
     AC_GEAR    NOSE        96.3   0.0  10.3 10000 2000  0.2   0.2 0.2  FIXED NONE 0 FIXED
     AC_GEAR    CABIN_LEFT   0.0 -25.0   0.0 10000 2000  0.2   0.2 0.2  FIXED NONE 0 FIXED
     AC_GEAR    CABIN_RIGHT  0.0  25.0   0.0 10000 2000  0.2   0.2 0.2  FIXED NONE 0 FIXED
     AC_GEAR    ROOF        41.3   0.0  53.3 10000 2000  0.2   0.2 0.2  FIXED NONE 0 FIXED
     AC_GEAR    LEFT_TIP    48.1 -222.0 18.9 10000 2000  0.2   0.2 0.2  FIXED NONE 0 FIXED
     AC_GEAR    RIGHT_TIP   48.1  222.0 18.9 10000 2000  0.2   0.2 0.2  FIXED NONE 0 FIXED

</UNDERCARRIAGE>

  <PROPULSION>

    <!--
      TANKS SECTION

      Tank locations and characteristics, empty weight, in aircraft's own coord system:
      X, Y, Z, in inches
      effective radius of tank, in inches (for fuel slosh, if/when modeled)
      capacity in pounds
      Current contents, in pounds

      ENGINE[S] SECTION

      Engine[s] is|are specified by giving engine name (which corresponds to an engine
      definition file in the "engines" directory) followed by x, y, z placement and
      pitch and yaw orientation. Coordinates are given in inches in the structural
      coordinate frame. Angles for pitch and yaw are specified in radians.

      AC_ENGINE name x y z pitch yaw

      THRUSTER[S] SECTION

      AC_THRUSTER name x y z pitch yaw

      The Cessna 310 does not have counter-rotating propellers.
    -->

    <AC_ENGINE FILE="engIO470D">
      XLOC  -27.5
      YLOC  -70.0
      ZLOC   15.5
      PITCH   0.0
      YAW     0.0
      FEED      0
      FEED      1
      FEED      2
      FEED      3
    </AC_ENGINE>

    <AC_ENGINE FILE="engIO470D">
      XLOC  -27.5
      YLOC   70.0
      ZLOC   15.5
      PITCH   0.0
      YAW     0.0
      FEED      0
      FEED      1
      FEED      2
      FEED      3
    </AC_ENGINE>

    <AC_THRUSTER FILE="propC10v">
      XLOC  -27.5
      YLOC  -70.0
      ZLOC   15.5
      PITCH   0.0
      YAW     0.0
      P_FACTOR 0.1
      SENSE   1.0
    </AC_THRUSTER>

    <AC_THRUSTER FILE="propC10v">
      XLOC  -27.5
      YLOC   70.0
      ZLOC   15.5
      PITCH   0.0
      YAW     0.0
      P_FACTOR 0.1
      SENSE   1.0
    </AC_THRUSTER>

    <!--
      Wing tip tanks
    -->

    <AC_TANK TYPE="FUEL" NUMBER="0">
      XLOC   35.0
      YLOC -209.8
      ZLOC   28.3
      RADIUS 13.3
      CAPACITY 336.0
      CONTENTS 225.0
    </AC_TANK>

    <AC_TANK TYPE="FUEL" NUMBER="1">
      XLOC   35.0
      YLOC  209.8
      ZLOC   28.3
      RADIUS 13.3
      CAPACITY 336.0
      CONTENTS 225.0
    </AC_TANK>

    <!--
      Wing locker tanks
    -->

    <AC_TANK TYPE="FUEL" NUMBER="2">
      XLOC   49.0
      YLOC   -41.6
      ZLOC   11.7
      RADIUS 29.4
      CAPACITY 135.0
      CONTENTS 95.0
    </AC_TANK>

    <AC_TANK TYPE="FUEL" NUMBER="3">
      XLOC   49.0
      YLOC   41.6
      ZLOC   11.7
      RADIUS 29.4
      CAPACITY 135.0
      CONTENTS 95.0
    </AC_TANK>

  </PROPULSION>

  <FLIGHT_CONTROL NAME="c310">

     <COMPONENT NAME="Pitch Trim Sum" TYPE="SUMMER">
       INPUT         fcs/elevator-cmd-norm
       INPUT         fcs/pitch-trim-cmd-norm
       CLIPTO        -1 1
     </COMPONENT>

     <COMPONENT NAME="Elevator Control" TYPE="AEROSURFACE_SCALE">
       INPUT         fcs/pitch-trim-sum
       MIN           -16.5
       MAX            15
       OUTPUT        fcs/elevator-pos-rad
       GAIN          0.01745
     </COMPONENT>

     <COMPONENT NAME="Roll Trim Sum" TYPE="SUMMER">
       INPUT         fcs/aileron-cmd-norm
       INPUT         fcs/roll-trim-cmd-norm
       CLIPTO        -1 1
     </COMPONENT>

     <COMPONENT NAME="Aileron Control" TYPE="AEROSURFACE_SCALE">
       INPUT         fcs/roll-trim-sum
       MIN           -20
       MAX            20
       GAIN          0.01745
       OUTPUT        fcs/left-aileron-pos-rad
     </COMPONENT>

     <COMPONENT NAME="Yaw Trim Sum" TYPE="SUMMER">
       INPUT         fcs/rudder-cmd-norm
       INPUT         fcs/yaw-trim-cmd-norm
       CLIPTO        -1 1
     </COMPONENT>

     <COMPONENT NAME="Rudder Control" TYPE="AEROSURFACE_SCALE">
       INPUT         fcs/yaw-trim-sum
       MIN           -29.3
       MAX           29.3
       GAIN          0.01745
       OUTPUT        fcs/rudder-pos-rad
     </COMPONENT>

     <COMPONENT NAME="Flaps Control" TYPE="KINEMAT">
       INPUT         fcs/flap-cmd-norm
       DETENTS       4
                     0    0
                     15   2
                     25   1
                     35   1
       OUTPUT        fcs/flap-pos-deg
     </COMPONENT>

     <COMPONENT NAME="Gear Control" TYPE="KINEMAT">
       INPUT        gear/gear-cmd-norm
       DETENTS      2
                    0    0
                    1    5
       OUTPUT       gear/gear-pos-norm
     </COMPONENT>

   </FLIGHT_CONTROL>

   <AERODYNAMICS>

     AC_ALPHALIMITS -0.087 0.28

     <AXIS NAME="LIFT">

       <GROUP NAME="CLb">
         Basic_lift

         <FACTOR NAME="kCLge" TYPE="VECTOR">
            Change_in_lift_due_to_ground_effect
            13
            aero/h_b-mac-ft
            none
            0.0   1.203
            0.1   1.127
            0.15  1.090
            0.2   1.073
            0.3   1.046
            0.4   1.055
            0.5   1.019
            0.6   1.013
            0.7   1.008
            0.8   1.006
            0.9   1.003
            1.0   1.002
            1.1   1.0
         </FACTOR>

         <COEFFICIENT NAME="CLo" TYPE="VALUE">
            Lift_at_zero_alpha
            aero/qbar-psf | metrics/Sw-sqft
            0.288
         </COEFFICIENT>

         <COEFFICIENT NAME="CLalpha" TYPE="VECTOR">
            Lift_due_to_alpha
            15
            aero/alpha-rad
            aero/qbar-psf | metrics/Sw-sqft
           -0.300 -1.010
           -0.282 -1.172
           -0.247 -1.087
           -0.212 -0.948
           -0.178 -0.810
            0.000  0.000
            0.104  0.476
            0.139  0.616
            0.174  0.754
            0.209  0.857
            0.244  0.947
            0.279  0.899
            0.300  0.806
            0.314  0.569
            0.349  0.288
          </COEFFICIENT>

          <COEFFICIENT NAME="CLDf" TYPE="VECTOR">
            Delta_lift_due_to_flap_deflection
            4
            fcs/flap-pos-deg
            aero/qbar-psf | metrics/Sw-sqft
            0   0
            15  0.065
            25  0.016
            35  0.254
          </COEFFICIENT>

       </GROUP>

       <COEFFICIENT NAME="CLDe" TYPE="VECTOR">
         Lift_due_to_Elevator_Deflection
         3
         aero/alpha-rad
         aero/qbar-psf | metrics/Sw-sqft | fcs/elevator-pos-rad
         0        0.81
         0.087266 0.90
         0.115192 0.77
       </COEFFICIENT>

       <COEFFICIENT NAME="CLadot" TYPE="VECTOR">
         Lift_due_to_alpha_rate
         3
         aero/alpha-rad
         aero/qbar-psf | metrics/Sw-sqft | aero/alphadot-rad_sec | aero/ci2vel
         0        5.3
         0.087266 4.5
         0.115192 4.1
       </COEFFICIENT>

       <COEFFICIENT NAME="CLq" TYPE="VECTOR">
         Lift_due_to_pitch_rate
         3
         aero/alpha-rad
         aero/qbar-psf | metrics/Sw-sqft | velocities/q-rad_sec | aero/ci2vel
         0        9.7
         0.087266 8.8
         0.115192 8.4
       </COEFFICIENT>

    </AXIS>

    <AXIS NAME="DRAG">

      <COEFFICIENT NAME="CDo" TYPE="VALUE">
         Drag_at_zero_lift
         aero/qbar-psf | metrics/Sw-sqft
         0.029
      </COEFFICIENT>

      <COEFFICIENT NAME="CDalpha" TYPE="VECTOR">
         Drag_due_to_alpha
         26
         aero/alpha-rad
         aero/qbar-psf | metrics/Sw-sqft
        -0.0872664   0.00407143
        -0.0698132   0.0013424
        -0.0523599   8.96747e-05
        -0.0349066   0.000313268
        -0.0174533   0.00201318
         0           0.0051894
         0.0174533   0.00993967
         0.0349066   0.0162201
         0.0523599   0.0240308
         0.0698132   0.0333717
         0.0872664   0.0442427
         0.10472     0.056644
         0.122173    0.0705754
         0.139626    0.086037
         0.15708     0.096239
         0.174533    0.106859
         0.191986    0.118034
         0.209439    0.129765
         0.226893    0.142366
         0.244346    0.156452
         0.261799    0.172732
         0.279253    0.178209
         0.296706    0.171598
         0.314159    0.161786
         0.331613    0.147493
         0.349066    0.109678
       </COEFFICIENT>

       <COEFFICIENT NAME="CDDf" TYPE="TABLE">
         Drag_due_to_flap_deflection
         26
         4
         aero/alpha-rad
         fcs/flap-pos-deg
         aero/qbar-psf | metrics/Sw-sqft
                    0         15          25          35
        -0.087266   0.000000   0.005967    0.026441    0.047301
        -0.069813   0.000000   0.009098    0.031138    0.052781
        -0.052360   0.000000   0.012230    0.035836    0.058261
        -0.034907   0.000000   0.015361    0.040533    0.063741
        -0.017453   0.000000   0.018493    0.045230    0.069221
         0.000000   0.000000   0.021624    0.049927    0.074702
         0.017453   0.000000   0.024812    0.054710    0.080281
         0.034907   0.000000   0.028001    0.059492    0.085860
         0.052360   0.000000   0.031189    0.064274    0.091439
         0.069813   0.000000   0.034377    0.069056    0.097019
         0.087266   0.000000   0.037565    0.073838    0.102598
         0.104720   0.000000   0.040753    0.078621    0.108177
         0.122173   0.000000   0.043942    0.083403    0.113757
         0.139626   0.000000   0.047129    0.088185    0.119336
         0.157080   0.000000   0.049078    0.091107    0.122745
         0.174533   0.000000   0.050998    0.093989    0.126107
         0.191986   0.000000   0.052920    0.096871    0.129469
         0.209439   0.000000   0.054841    0.099752    0.132831
         0.226893   0.000000   0.056810    0.102706    0.136277
         0.244346   0.000000   0.058911    0.105858    0.139954
         0.261799   0.000000   0.061224    0.109327    0.144001
         0.279253   0.000000   0.061978    0.110458    0.145320
         0.296706   0.000000   0.061067    0.109092    0.143727
         0.314159   0.000000   0.059682    0.107014    0.141303
         0.331613   0.000000   0.057587    0.103871    0.137636
         0.349066   0.000000   0.051493    0.094730    0.126971
      </COEFFICIENT>

       <COEFFICIENT NAME="CDDe" TYPE="VALUE">
         Drag_due_to_Elevator_Deflection
         aero/qbar-psf | metrics/Sw-sqft | fcs/mag-elevator-pos-rad
         0
       </COEFFICIENT>

       <COEFFICIENT NAME="CDbeta" TYPE="VALUE">
         Drag_due_to_sideslip
         aero/qbar-psf | metrics/Sw-sqft | aero/mag-beta-rad
         0.14
       </COEFFICIENT>

       <COEFFICIENT NAME="CDgear" TYPE="VALUE">
         Drag_due_to_landing_gear
         aero/qbar-psf | metrics/Sw-sqft | gear/gear-pos-norm
         0.03
       </COEFFICIENT>

    </AXIS>

    <AXIS NAME="SIDE">

      <COEFFICIENT NAME="CYb" TYPE="VECTOR">
        Side_force_due_to_beta
        3
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | aero/beta-rad
         0        -0.698
         0.087266 -0.610
         0.115192 -0.577
      </COEFFICIENT>

      <COEFFICIENT NAME="CYp" TYPE="VECTOR">
        Side_force_due_to_roll_rate
        3
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | aero/bi2vel | velocities/p-rad_sec
         0        -0.1410
         0.087266 -0.2093
         0.115192 -0.2897
      </COEFFICIENT>

      <COEFFICIENT NAME="CYr" TYPE="VALUE">
        Side_force_due_to_yaw_rate
        aero/qbar-psf | metrics/Sw-sqft | aero/bi2vel | velocities/r-rad_sec
         0.355
      </COEFFICIENT>

      <COEFFICIENT NAME="CYDa" TYPE="VALUE">
        Side_force_due_to_aileron
        aero/qbar-psf | metrics/Sw-sqft | fcs/left-aileron-pos-rad
         0
      </COEFFICIENT>

      <COEFFICIENT NAME="CYDr" TYPE="VALUE">
        Side_force_due_to_rudder
        aero/qbar-psf | metrics/Sw-sqft | fcs/rudder-pos-rad
         0.230
      </COEFFICIENT>

    </AXIS>

    <AXIS NAME="ROLL">

      <COEFFICIENT NAME="Clb" TYPE="TABLE">
        Roll_moment_due_to_beta
        3
        3
        aero/beta-rad
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft
                0       0.087266  0.115192
        -0.349  0.0382  0.0322    0.0323
         0      0       0         0
         0.349 -0.0382 -0.0322   -0.0323
      </COEFFICIENT>

      <COEFFICIENT NAME="Clp" TYPE="VECTOR">
        Roll_moment_due_to_roll_rate_(roll_damping)
        3
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/p-rad_sec
         0        -0.551
         0.087266 -0.552
         0.115192 -0.566
      </COEFFICIENT>

      <COEFFICIENT NAME="Clr" TYPE="VECTOR">
        Roll_moment_due_to_yaw_rate
        3
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/r-rad_sec
         0        0.0729
         0.087266 0.1746
         0.115192 0.2433
      </COEFFICIENT>

      <COEFFICIENT NAME="ClDa" TYPE="VALUE">
        Roll_moment_due_to_aileron
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
         0.1720
      </COEFFICIENT>

      <COEFFICIENT NAME="Cldr" TYPE="VALUE">
        Roll_moment_due_to_rudder
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
         0.0192
      </COEFFICIENT>

    </AXIS>

    <AXIS NAME="PITCH">

      <COEFFICIENT NAME="Cmo" TYPE="VALUE">
        Pitch_moment_at_zero_alpha
        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft
        0.07
      </COEFFICIENT>

      <COEFFICIENT NAME="Cmalpha" TYPE="VECTOR">
        Pitch_moment_due_to_alpha
        3
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/alpha-rad
         0        -0.137
         0.087266 -0.339
         0.115192 -0.619
      </COEFFICIENT>

      <COEFFICIENT NAME="Cmadot" TYPE="VECTOR">
        Pitch_moment_due_to_alpha_rate
        3
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/ci2vel | aero/alphadot-rad_sec
         0        -12.7
         0.087266 -14.8
         0.115192 -11.4
      </COEFFICIENT>

      <COEFFICIENT NAME="Cmq" TYPE="VECTOR">
        Pitch_moment_due_to_pitch_rate
        3
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/ci2vel | velocities/q-rad_sec
         0        -26.3
         0.087266 -29.2
         0.115192 -25.1
      </COEFFICIENT>

      <COEFFICIENT NAME="CmDe" TYPE="VECTOR">
        Pitch_moment_due_to_elevator_deflection
        3
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | fcs/elevator-pos-rad
         0        -2.26
         0.087266 -2.53
         0.115192 -2.16
      </COEFFICIENT>

      <COEFFICIENT NAME="CmDf" TYPE="VECTOR">
        Pitch_moment_due_to_flap_deflection
        4
        fcs/flap-pos-deg
        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft
         0    0
         15  -0.0654
         25  -0.0981
         35  -0.1140
      </COEFFICIENT>

    </AXIS>

    <AXIS NAME="YAW">

      <COEFFICIENT NAME="Cnb" TYPE="VECTOR">
        Yaw_moment_due_to_beta
        3
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/beta-rad
         0        0.1444
         0.087266 0.1552
         0.115192 0.1683
      </COEFFICIENT>

      <COEFFICIENT NAME="Cnp" TYPE="VECTOR">
        Yaw_moment_due_to_roll_rate
        3
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/p-rad_sec
         0        -0.0257
         0.087266 -0.0615
         0.115192 -0.1021
       </COEFFICIENT>

      <COEFFICIENT NAME="Cnr" TYPE="VECTOR">
        Yaw_moment_due_to_yaw_rate
        3
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/r-rad_sec
         0        -0.1495
         0.087266 -0.1561
         0.115192 -0.1947
      </COEFFICIENT>

      <COEFFICIENT NAME="CnDa" TYPE="VECTOR">
        Yaw_moment_due_to_aileron
        3
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
         0        -0.0168
         0.087266 -0.0402
         0.115192 -0.0676
      </COEFFICIENT>

      <COEFFICIENT NAME="CnDr" TYPE="VALUE">
        Yaw_moment_due_to_rudder
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
        -0.1152
      </COEFFICIENT>

    </AXIS>

  </AERODYNAMICS>

  <!--
    OUTPUT section definition

    The following specifies the way that JSBSim writes out data.

    NAME is the filename you want the output to go to

    TYPE can be:
      CSV       Comma separated data. If a filename is supplied then the data
                goes to that file. If COUT or cout is specified, the data goes
                to stdout. If the filename is a null filename the data goes to
                stdout, as well.
      SOCKET    Will eventually send data to a socket output, where NAME
                would then be the IP address of the machine the data should be
                sent to. DON'T USE THIS YET!
      TABULAR   Columnar data. NOT IMPLEMENTED YET!
      TERMINAL  Output to terminal. NOT IMPLEMENTED YET!
      NONE      Specifies to do nothing. THis setting makes it easy to turn on and
                off the data output without having to mess with anything else.

    The arguments that can be supplied, currently, are

    RATE_IN_HZ  An integer rate in times-per-second that the data is output. This
                value may not be *exactly* what you want, due to the dependence
                on dt, the cycle rate for the FDM.

    The following parameters tell which subsystems of data to output:

    SIMULATION       ON|OFF
    ATMOSPHERE       ON|OFF
    MASSPROPS        ON|OFF
    AEROSURFACES     ON|OFF
    RATES            ON|OFF
    VELOCITIES       ON|OFF
    FORCES           ON|OFF
    MOMENTS          ON|OFF
    POSITION         ON|OFF
    COEFFICIENTS     ON|OFF
    GROUND_REACTIONS ON|OFF
    FCS              ON|OFF
    PROPULSION       ON|OFF

    NOTE that Time is always output with the data.
  -->
  <OUTPUT NAME="JSBout310.csv" TYPE="NONE">
    RATE_IN_HZ       10
    SIMULATION       OFF
    ATMOSPHERE       OFF
    MASSPROPS        ON
    AEROSURFACES     ON
    RATES            ON
    VELOCITIES       ON
    FORCES           ON
    MOMENTS          ON
    POSITION         ON
    COEFFICIENTS     ON
    GROUND_REACTIONS ON
    FCS              ON
    PROPULSION       ON
  </OUTPUT>
</FDM_CONFIG>


