<FDM_CONFIG NAME="c172" VERSION="1.60">
<!--
  File:        c172p.xml
  Author:      David Megginson (based on c172r.xml by Tony Peden)
  CVS Version: $Id: c172p.xml,v 1.6 2002/11/27 17:49:38 david Exp $

  Function: Models a 1981 Cessna 172P.

  Sources:
    Tony Peden, c172r.xml, JSBSim (http://jsbsim.sourceforge.net/).
    Jan Roskam, Airplane Flight Dynamics and Automatic Flight
      Controls.  Part I.  DARcorporation, 1995.

  Notes:

    Roskam's data is for a 182, not a 172, but it should be close
    enough.  He gives linear coefficients for three states:

    1. Climb (5.4 deg alpha).
    2. Cruise (0 deg alpha).
    3. Approach (4 deg alpha, and presumably, full flaps).

    I have extrapolated small tables from this data to account for the
    effects of flaps and alpha, especially in the lateral coefficients.
-->

  <METRICS>
    <!--
    // 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
    // Iyy
    // Izz
    // Ixz
    // Empty weight
    // 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  174   <!-- square feet -->
    AC_WINGSPAN  35.8  <!-- ft          -->
    AC_CHORD     4.9   <!-- ft          -->
    AC_HTAILAREA 21.9  <!-- square feet -->
    AC_HTAILARM  15.7  <!-- ft          -->
    AC_VTAILAREA 16.5  <!-- square feet -->
    AC_LV        15.7  <!-- ft          -->
    AC_IXX    948
    AC_IYY    1346
    AC_IZZ    1967
    AC_IXZ    0
    AC_EMPTYWT   1500
    AC_AERORP    43.2  0.0 59.4
    AC_CGLOC     41.0  0.0 36.5
<!-- Pilot -->
    AC_POINTMASS 180.0 36.0 -14.0 24.0
<!-- Co-pilot -->
<!-- AC_POINTMASS 180.0 36.0  14.0 24.0 -->
    AC_EYEPTLOC  37.0  0.0 48.0

  </METRICS>

  <UNDERCARRIAGE>

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

    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
    <retraction attribute>           <RETRACT | FIXED>
    -->

     AC_GEAR  NOSE        -6.8   0.0 -20.0  1800  600  0.5  0.8 0.02 STEERABLE NOSE 20 FIXED
     AC_GEAR  LEFT_MAIN   58.2 -43.0 -17.9  5400 1600  0.5  0.8 0.02 FIXED  LEFT  0 FIXED
     AC_GEAR  RIGHT_MAIN  58.2  43.0 -17.9  5400 1600  0.5  0.8 0.02 FIXED  RIGHT 0 FIXED
     AC_GEAR  TAIL_SKID  188.0  0.0    8.0 20000 1000  0.2   0.2 0.2  FIXED NONE 0 FIXED
     AC_GEAR  LEFT_TIP    43.2 -214.8 59.4 10000 2000  0.2   0.2 0.2  FIXED NONE 0 FIXED
     AC_GEAR  RIGHT_TIP   43.2  214.8 59.4 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
    -->

    <AC_ENGINE FILE="eng_io320">
      XLOC  -19.7
      YLOC    0.0
      ZLOC   26.6
      PITCH   0.0
      YAW     0.0
      FEED      0
      FEED      1
    </AC_ENGINE>

    <AC_THRUSTER FILE="prop_75in2f">
      XLOC  -37.7
      YLOC    0.0
      ZLOC   26.6
      PITCH   0.0
      YAW     0
      P_FACTOR 10.0
      SENSE   1.0
    </AC_THRUSTER>

    <AC_TANK TYPE="FUEL" NUMBER="0">
      XLOC   56.0
      YLOC -112.0
      ZLOC   59.4
      RADIUS 29.4
      CAPACITY 185.0
      CONTENTS 100.0
    </AC_TANK>

    <AC_TANK TYPE="FUEL" NUMBER="1">
      XLOC   56.0
      YLOC  112.0
      ZLOC   59.4
      RADIUS 29.4
      CAPACITY 185.0
      CONTENTS 100.0
    </AC_TANK>

  </PROPULSION>


  <FLIGHT_CONTROL NAME="c172">
    <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          -28
       MAX           23
       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="Left Aileron Control" TYPE="AEROSURFACE_SCALE">
       INPUT         fcs/roll-trim-sum
       MIN          -20
       MAX           15
       GAIN          0.01745
       OUTPUT        fcs/left-aileron-pos-rad
     </COMPONENT>
      <COMPONENT NAME="Right Aileron Control" TYPE="AEROSURFACE_SCALE">
       INPUT         fcs/roll-trim-sum
       MIN          -20
       MAX           15
       INVERT
       GAIN          0.01745
       OUTPUT        fcs/right-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         -16
       MAX          16
       GAIN         0.01745
       OUTPUT       fcs/rudder-pos-rad
     </COMPONENT>
     <COMPONENT NAME="Flaps Control" TYPE="KINEMAT">
       INPUT        fcs/flap-cmd-norm
       DETENTS      4
                    0    0
                    10   2
                    20   1
                    30   1
       OUTPUT      fcs/flap-pos-deg
     </COMPONENT>
   </FLIGHT_CONTROL>

   <AERODYNAMICS>

     AC_ALPHALIMITS -0.087 0.28
     AC_HYSTLIMITS   0.09  0.36

    <AXIS NAME="LIFT">

      <GROUP NAME="CLb">
        Basic_lift

        <!-- Peden -->
        <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>

        <!-- Peden -->
        <COEFFICIENT NAME="CLwbh" TYPE="TABLE">
          Lift_due_to_alpha
          17
          2
          aero/alpha-rad
          aero/stall-hyst-norm
          aero/qbar-psf | metrics/Sw-sqft
                 0     1
          -0.09 -0.22 -0.22
           0     0.25  0.25
           0.09  0.73  0.73    
           0.1   0.83  0.78
           0.12  0.92  0.79    
           0.14  1.02  0.81
           0.16  1.08  0.82    
           0.17  1.13  0.83  
           0.19  1.19  0.85  
           0.21  1.25  0.86
           0.24  1.35  0.88
           0.26  1.44  0.9 
           0.28  1.47  0.92
           0.3   1.43  0.95
           0.32  1.38  0.99
           0.34  1.3   1.05  
           0.36  1.15  1.15
         </COEFFICIENT>

         <!-- Peden -->
         <COEFFICIENT NAME="CLDf" TYPE="VECTOR">
           Delta_lift_due_to_flap_deflection
           4
           fcs/flap-pos-deg
           aero/qbar-psf | metrics/Sw-sqft
           0   0
           10  0.20
           20  0.30
           30  0.35
        </COEFFICIENT>

      </GROUP>

      <!-- Roskam p.481 -->
      <COEFFICIENT NAME="CLDe" TYPE="VALUE">
        Lift_due_to_Elevator_Deflection
        aero/qbar-psf | metrics/Sw-sqft | fcs/elevator-pos-rad
        0.43
      </COEFFICIENT>

      <!-- Roskam p.481 -->
      <COEFFICIENT NAME="CLadot" TYPE="VALUE">
        Lift_due_to_alpha_rate
        aero/qbar-psf | metrics/Sw-sqft | aero/alphadot-rad_sec | aero/ci2vel
        1.7
      </COEFFICIENT>

      <!-- Roskam p.481 -->
      <COEFFICIENT NAME="CLq" TYPE="VALUE">
        Lift_due_to_pitch_rate
        aero/qbar-psf | metrics/Sw-sqft | velocities/q-aero-rad_sec | aero/ci2vel
        3.9
      </COEFFICIENT>

    </AXIS>

    <AXIS NAME="DRAG">

      <!-- Roskam p.481 -->
      <COEFFICIENT NAME="CDo" TYPE="VALUE">
        Drag_at_zero_lift
        aero/qbar-psf | metrics/Sw-sqft
        0.0270
      </COEFFICIENT>

      <GROUP NAME="CDb">
         Basic_drag

         <!-- Peden -->
         <FACTOR NAME="kCDge" TYPE="VECTOR">
            Change_in_drag_due_to_ground_effect
            13
            aero/h_b-mac-ft
            none
            0.0   0.048
            0.1   0.515
            0.15  0.629
            0.2   0.709
            0.3   0.815
            0.4   0.882
            0.5   0.928
            0.6   0.962
            0.7   0.988
            0.8   1.0
            0.9   1.0
            1.0   1.0
            1.1   1.0
         </FACTOR>

         <!-- Peden -->
         <COEFFICIENT NAME="CDDf" TYPE="VECTOR">
           Delta_drag_due_to_flap_deflection
           4
           fcs/flap-pos-deg
           aero/qbar-psf | metrics/Sw-sqft
           0   0
           10  0.007
           20  0.012
           30  0.018
         </COEFFICIENT>

         <!-- Peden -->
         <COEFFICIENT NAME="CDwbh" TYPE="TABLE">
           Drag_due_to_alpha
           26
           4
           aero/alpha-rad
           fcs/flap-pos-deg
           aero/qbar-psf | metrics/Sw-sqft
                      0             10             20             30
          -0.0872664  0.00407143    3.8165e-05     0.000512444    0.00137231
          -0.0698132  0.0013424     0.000440634    0.00248067     0.00412341
          -0.0523599  8.96747e-05   0.00231942     0.0059252      0.00835082
          -0.0349066  0.000313268   0.00567451     0.0108461      0.0140545
          -0.0174533  0.00201318    0.0105059      0.0172432      0.0212346
          0           0.0051894     0.0168137      0.0251167      0.0298909
          0.0174533   0.00993967    0.0247521      0.0346492      0.0402205
          0.0349066   0.0162201     0.0342207      0.0457119      0.0520802
          0.0523599   0.0240308     0.0452195      0.0583047      0.0654701
          0.0698132   0.0333717     0.0577485      0.0724278      0.0803902
          0.0872664   0.0442427     0.0718077      0.088081       0.0968405
          0.10472     0.056644      0.0873971      0.105265       0.114821
          0.122173    0.0705754     0.104517       0.123978       0.134332
          0.139626    0.086037      0.123166       0.144222       0.155373
          0.15708     0.096239      0.135317       0.157346       0.168984
          0.174533    0.106859      0.147857       0.170848       0.182966
          0.191986    0.118034      0.160954       0.184905       0.197503
          0.209439    0.129765      0.174606       0.199517       0.212596
          0.226893    0.142366      0.189176       0.215072       0.228643
          0.244346    0.156452      0.205363       0.23231        0.246406
          0.261799    0.172732      0.223956       0.252059       0.266733
          0.279253    0.178209      0.230187       0.258667       0.273529
          0.296706    0.171598      0.222665       0.25069        0.265325
          0.314159    0.161786      0.211468       0.2388         0.253089
          0.331613    0.147493      0.19508        0.221364       0.235129
          0.349066    0.109678      0.151171       0.174408       0.186649
        </COEFFICIENT>

      </GROUP>  

      <!-- Roskam p.481 -->
      <COEFFICIENT NAME="CDDe" TYPE="VALUE">
        Drag_due_to_Elevator_Deflection
        aero/qbar-psf | metrics/Sw-sqft | fcs/mag-elevator-pos-rad
        0
      </COEFFICIENT>

      <!-- Peden -->
      <COEFFICIENT NAME="CDbeta" TYPE="VALUE">
        Drag_due_to_sideslip
        aero/qbar-psf | metrics/Sw-sqft | aero/mag-beta-rad
        0.17
      </COEFFICIENT>

    </AXIS>

    <AXIS NAME="SIDE">

      <!-- based on Roskam p.482, clamped to +/-20deg beta -->
      <COEFFICIENT NAME="CYb" TYPE="TABLE">
        Side_force_due_to_beta
        3
        2
        aero/beta-rad
        fcs/flap-pos-deg
        aero/qbar-psf | metrics/Sw-sqft
                 0     30
        -0.349   0.137  0.106
         0       0      0
         0.349  -0.137 -0.106
      </COEFFICIENT>

      <!-- Roskam p.482 -->
      <COEFFICIENT NAME="CYda" TYPE="VALUE">
        Side_force_due_to_aileron
        aero/qbar-psf | metrics/Sw-sqft | fcs/left-aileron-pos-rad
        0
      </COEFFICIENT>

      <!-- Roskam p.482 -->
      <COEFFICIENT NAME="CYdr" TYPE="VALUE">
        Side_force_due_to_rudder
        aero/qbar-psf | metrics/Sw-sqft | fcs/rudder-pos-rad
        0.187
      </COEFFICIENT>

      <!-- based on Roskam p.482 -->
      <COEFFICIENT NAME="CYp" TYPE="TABLE">
        Side_force_due_to_roll_rate
        2
        2
        aero/alpha-rad
        fcs/flap-pos-deg
        aero/qbar-psf | metrics/Sw-sqft | aero/bi2vel | velocities/p-aero-rad_sec
               0      30
        0.000 -0.075  -0.161
        0.094 -0.145  -0.231
      </COEFFICIENT>

      <!-- based on Roskam p.482 -->
      <COEFFICIENT NAME="CYr" TYPE="TABLE">
        Side_force_due_to_yaw_rate
        2
        2
        aero/alpha-rad
        fcs/flap-pos-deg
        aero/qbar-psf | metrics/Sw-sqft | aero/bi2vel | velocities/r-aero-rad_sec
              0      30
        0.000 0.214  0.162
        0.094 0.267  0.215
      </COEFFICIENT>

    </AXIS>

    <AXIS NAME="ROLL">

      <!-- based on Roskam p.482, clamped to +/-20deg beta -->
      <COEFFICIENT NAME="Clb" TYPE="VECTOR">
        Roll_moment_due_to_beta
        3
        aero/beta-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft
        -0.349  0.0322
         0      0
         0.349 -0.0322
      </COEFFICIENT>

      <!-- Roskam p.482 -->
      <COEFFICIENT NAME="Clp" TYPE="VALUE">
        Roll_moment_due_to_roll_rate_(roll_damping)
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/p-aero-rad_sec
        -0.484
      </COEFFICIENT>

      <!-- based on Roskam p.482 -->
      <COEFFICIENT NAME="Clr" TYPE="TABLE">
        Roll_moment_due_to_yaw_rate
        2
        2
        aero/alpha-rad
        fcs/flap-pos-deg
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/r-aero-rad_sec
              0      30
        0.000 0.0798  0.1246
        0.094 0.1869  0.2317
      </COEFFICIENT>

      <!-- Roskam p.482 -->
      <COEFFICIENT NAME="ClDa" TYPE="VALUE">
        Roll_moment_due_to_aileron
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
        0.229
      </COEFFICIENT>

      <!-- Roskam p.482 -->
      <COEFFICIENT NAME="Cldr" TYPE="VALUE">
        Roll_moment_due_to_rudder
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
        0.0147
      </COEFFICIENT>

    </AXIS>

    <AXIS NAME="PITCH">

      <!-- Roskam p.481 -->
      <COEFFICIENT NAME="Cmo" TYPE="VECTOR">
        Pitching_moment_at_zero_alpha
        2
        fcs/flap-pos-deg
        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft
        0  0.04
        30 0.09
      </COEFFICIENT>

      <!-- based on Roskam p.481 -->
      <COEFFICIENT NAME="Cmalpha" TYPE="TABLE">
        Pitch_moment_due_to_alpha
        2
        2
        aero/alpha-rad
        fcs/flap-pos-deg
        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/alpha-rad
                 0     30
         0      -0.613 -0.584
         0.0943 -0.650 -0.621
      </COEFFICIENT>

      <!-- based on Roskam p.481 -->
      <COEFFICIENT NAME="Cmq" TYPE="TABLE">
         Pitch_moment_due_to_pitch_rate
         2
         2
         aero/alpha-rad
         fcs/flap-pos-deg
         aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/ci2vel | velocities/q-aero-rad_sec
                 0     30
         0      -12.4  -9.3
         0.0943 -15.2 -12.1
      </COEFFICIENT>

      <!-- based on Roskam p.481 -->
      <COEFFICIENT NAME="Cmadot" TYPE="TABLE">
        Pitch_moment_due_to_alpha_rate
        2
        2
        aero/alpha-rad
        fcs/flap-pos-deg
        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/ci2vel | aero/alphadot-rad_sec
                0    30
        0      -7.27 -6.66
        0.0943 -5.57 -4.96
      </COEFFICIENT>

      <!-- based on Roskam p.481 -->
      <COEFFICIENT NAME="Cmde" TYPE="TABLE">
        Pitch_moment_due_to_elevator_deflection
        2
        2
        aero/alpha-rad
        fcs/flap-pos-deg
        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | fcs/elevator-pos-rad
                0     30
        0      -1.122 -0.846
        0.0943 -1.369 -1.093
      </COEFFICIENT>

    </AXIS>

    <AXIS NAME="YAW">

      <!-- based on Roskam p.482, clamped to +/-20deg beta -->
      <COEFFICIENT NAME="Cnb" TYPE="TABLE">
        Yaw_moment_due_to_beta
        3
        2
        aero/beta-rad
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft
                0       0.0943
        -0.349 -0.0205 -0.0317
         0      0       0
         0.349  0.0205  0.0317
      </COEFFICIENT>

      <!-- based on Roskam p.482 -->
      <COEFFICIENT NAME="Cnp" TYPE="TABLE">
        Yaw_moment_due_to_roll_rate
        2
        2
        aero/alpha-rad
        fcs/flap-pos-deg
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/p-aero-rad_sec
                0       30
        0      -0.0278  -0.0685
        0.0943 -0.0649  -0.1056
      </COEFFICIENT>

      <!-- Roskam p.482 -->
      <COEFFICIENT NAME="Cnr" TYPE="VECTOR">
        Yaw_moment_due_to_yaw_rate
        2
        aero/alpha-rad
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/r-aero-rad_sec
        0      -0.0937
        0.0943 -0.1199
      </COEFFICIENT>

      <!-- based on Roskam p.482 -->
      <COEFFICIENT NAME="Cnda" TYPE="VECTOR">
        Yaw_moment_due_to_aileron
        2
        fcs/flap-pos-deg
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
        0  -0.0216
        30 -0.0573
      </COEFFICIENT>

      <!-- based on Roskam p.482 -->
      <COEFFICIENT NAME="Cndr" TYPE="VECTOR">
        Yaw_moment_due_to_rudder
        2
        fcs/flap-pos-deg
        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
        0  -0.0645
        30 -0.0485
      </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="JSBout172.csv" TYPE="CSV">
    RATE_IN_HZ       20
    SIMULATION       OFF
    ATMOSPHERE       ON
    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>
