diff --git a/Aircraft/c172p/Engines/eng_io320.xml b/Aircraft/c172p/Engines/eng_io320.xml
index 7b8a09105..2e036a35f 100644
--- a/Aircraft/c172p/Engines/eng_io320.xml
+++ b/Aircraft/c172p/Engines/eng_io320.xml
@@ -1,12 +1,23 @@
 <?xml version="1.0"?>
-<FG_PISTON NAME="IO320">
-  MINMP             6.5
-  MAXMP            29.92
-  DISPLACEMENT    320.0
-  MAXHP           160.0
-  CYCLES            2.0
-  IDLERPM         550.0
-  MAXTHROTTLE       1.0
-  MINTHROTTLE       0.2
-</FG_PISTON>
+<!--
+  File:     IO320.xml
+  Author:   Aero-Matic v 0.8
 
+  Inputs:
+    name:           IO320
+    type:           piston
+    power:          160.0 hp
+    augmented?      no
+    injected?       no
+-->
+
+<piston_engine name="IO320">
+  <minmp unit="INHG">          6.5 </minmp>
+  <maxmp unit="INHG">         29.92 </maxmp>
+  <displacement unit="IN3"> 320.00 </displacement>
+  <maxhp>        160.00 </maxhp>
+  <cycles>         2.0 </cycles>
+  <idlerpm>      550.0 </idlerpm>
+  <maxthrottle>    1.0 </maxthrottle>
+  <minthrottle>    0.2 </minthrottle>
+</piston_engine>
diff --git a/Aircraft/c172p/Engines/prop_75in2f.xml b/Aircraft/c172p/Engines/prop_75in2f.xml
index 8217ca660..3109f71c7 100644
--- a/Aircraft/c172p/Engines/prop_75in2f.xml
+++ b/Aircraft/c172p/Engines/prop_75in2f.xml
@@ -1,61 +1,71 @@
 <?xml version="1.0"?>
-<FG_PROPELLER  NAME="Fixed-Pitch 75-inch Two-Blade Propeller">
-  IXX       1.67
-  DIAMETER  75
-  NUMBLADES  2
-  MINPITCH 22
-  MAXPITCH 22
-  C_THRUST 25 1 
-  0.0   0.068
-  0.1   0.068
-  0.2   0.067
-  0.3   0.066
-  0.4   0.064
-  0.5   0.061
-  0.6   0.057
-  0.7   0.050
-  0.8   0.040
-  0.9   0.029
-  1.0   0.019
-  1.1   0.008
-  1.2   -0.001
-  1.3   -0.008
-  1.4   -0.019
-  1.5   -0.029
-  1.6   -0.040
-  1.7   -0.050
-  1.8   -0.057
-  1.9   -0.061
-  2.0   -0.064
-  2.1   -0.066
-  2.2   -0.067
-  2.3   -0.068
-  5.0   -0.068
-  C_POWER 26 1  
-  0.0   0.0580
-  0.1   0.0620
-  0.2   0.0600
-  0.3   0.0580
-  0.4   0.0520
-  0.5   0.0450
-  0.6   0.0421
-  0.7   0.0389
-  0.8   0.0346
-  0.9   0.0280
-  1.0   0.0202
-  1.1   0.0111
-  1.2   0.0075
-  1.3   0.0111
-  1.4   0.0202
-  1.5   0.0280
-  1.6   0.0346
-  1.7   0.0389
-  1.8   0.0421
-  1.9   0.0436
-  2.0   0.0445
-  2.1   0.0445
-  2.2   0.0442
-  2.3   0.0431
-  2.4   0.0424
-  5.0   0.0413
-</FG_PROPELLER>
+
+<propeller name="Fixed-Pitch 75-inch Two-Blade Propeller">
+  <ixx> 1.67 </ixx>
+  <diameter unit="IN"> 75.0 </diameter>
+  <numblades> 2 </numblades>
+  <minpitch> 22 </minpitch>
+  <maxpitch> 22 </maxpitch>
+
+  <table name="C_THRUST" type="internal">
+    <tableData>
+      0.0   0.068
+      0.1   0.068
+      0.2   0.067
+      0.3   0.066
+      0.4   0.064
+      0.5   0.061
+      0.6   0.057
+      0.7   0.050
+      0.8   0.040
+      0.9   0.029
+      1.0   0.019
+      1.1   0.008
+      1.2   -0.001
+      1.3   -0.008
+      1.4   -0.019
+      1.5   -0.029
+      1.6   -0.040
+      1.7   -0.050
+      1.8   -0.057
+      1.9   -0.061
+      2.0   -0.064
+      2.1   -0.066
+      2.2   -0.067
+      2.3   -0.068
+      5.0   -0.068
+    </tableData>
+  </table>
+
+  <table name="C_POWER" type = "internal">
+    <tableData>
+      0.0   0.0580
+      0.1   0.0620
+      0.2   0.0600
+      0.3   0.0580
+      0.4   0.0520
+      0.5   0.0450
+      0.6   0.0421
+      0.7   0.0389
+      0.8   0.0346
+      0.9   0.0280
+      1.0   0.0202
+      1.1   0.0111
+      1.2   0.0075
+      1.3   0.0111
+      1.4   0.0202
+      1.5   0.0280
+      1.6   0.0346
+      1.7   0.0389
+      1.8   0.0421
+      1.9   0.0436
+      2.0   0.0445
+      2.1   0.0445
+      2.2   0.0442
+      2.3   0.0431
+      2.4   0.0424
+      5.0   0.0413
+    </tableData>
+  </table>
+
+</propeller>
diff --git a/Aircraft/c172p/c172p.xml b/Aircraft/c172p/c172p.xml
index be25f2380..e080ffee2 100644
--- a/Aircraft/c172p/c172p.xml
+++ b/Aircraft/c172p/c172p.xml
@@ -1,677 +1,791 @@
-<FDM_CONFIG NAME="c172" VERSION="1.65">
-<!--
-  File:        c172p.xml
-  Author:      David Megginson (based on c172r.xml by Tony Peden)
-  CVS Version: $Id$
-
-  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
-    AC_VRP       42.6  0.0 38.5
-  </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 NONE 10 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_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_ENGINE>
-
-    <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
-       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">
-
-      <!-- Peden -->
-      <COEFFICIENT NAME="Cmo" TYPE="VALUE">
-        Pitching_moment_at_zero_alpha
-        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft
-        0.1
-      </COEFFICIENT>
-
-      <!-- Peden -->
-      <COEFFICIENT NAME="Cmalpha" TYPE="VALUE">
-        Pitch_moment_due_to_alpha
-        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/alpha-rad
-        -1.8
-      </COEFFICIENT>
-
-      <!-- Roskam p.481 -->
-      <COEFFICIENT NAME="Cmq" TYPE="VALUE">
-         Pitch_moment_due_to_pitch_rate
-         aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/ci2vel | velocities/q-aero-rad_sec
-         -12.4
-      </COEFFICIENT>
-
-      <!-- based on Roskam p.481 -->
-      <COEFFICIENT NAME="Cmadot" TYPE="VALUE">
-        Pitch_moment_due_to_alpha_rate
-        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/ci2vel | aero/alphadot-rad_sec
-        -7.27
-      </COEFFICIENT>
-
-      <!-- Roskam p.481 -->
-      <COEFFICIENT NAME="Cmde" TYPE="VALUE">
-        Pitch_moment_due_to_elevator_deflection
-        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | fcs/elevator-pos-rad
-        -1.122
-      </COEFFICIENT>
-
-      <!-- Peden -->
-      <COEFFICIENT NAME="Cmdf" TYPE="VECTOR">
-        Delta_pitching_moment_due_to_flap_deflection
-        4
-        fcs/flap-pos-deg
-        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft
-        0    0
-        10  -0.0654
-        20  -0.0981
-        30  -0.1140
-       </COEFFICIENT>
-
-    </AXIS>
-
-    <AXIS NAME="YAW">
-
-      <!-- based on Roskam p.482, clamped to +/-20deg beta -->
-      <COEFFICIENT NAME="Cnb" TYPE="VECTOR">
-        Yaw_moment_due_to_beta
-        3
-        aero/beta-rad
-        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft
-        -0.349 -0.0205
-         0      0
-         0.349  0.0205
-      </COEFFICIENT>
-
-      <!-- Roskam p.482 -->
-      <COEFFICIENT NAME="Cnp" TYPE="VALUE">
-        Yaw_moment_due_to_roll_rate
-        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/p-aero-rad_sec
-        -0.0278
-      </COEFFICIENT>
-
-      <!-- Roskam p.482 -->
-      <COEFFICIENT NAME="Cnr" TYPE="VALUE">
-        Yaw_moment_due_to_yaw_rate
-        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/r-aero-rad_sec
-        -0.0937
-      </COEFFICIENT>
-
-      <!-- Peden -->
-      <COEFFICIENT NAME="Cnda" TYPE="VALUE">
-        Yaw_moment_due_to_aileron
-        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
-        -0.0053
-      </COEFFICIENT>
-
-      <!-- Peden -->
-      <COEFFICIENT NAME="Cndr" TYPE="VALUE">
-        Yaw_moment_due_to_rudder
-        aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
-        -0.043
-      </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="NONE">
-    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>
+<?xml version="1.0"?>
+<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
+<fdm_config name="c172" version="2.0" release="BETA"
+    xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
+    xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
+
+    <fileheader>
+        <author> Unknown </author>
+        <filecreationdate> 2002-01-01 </filecreationdate>
+        <version> $Id$ </version>
+        <description> Cessna C-172 </description>
+    </fileheader>
+
+    <metrics>
+        <wingarea unit="FT2"> 174 </wingarea>
+        <wingspan unit="FT"> 35.8 </wingspan>
+        <chord unit="FT"> 4.9 </chord>
+        <htailarea unit="FT2"> 21.9 </htailarea>
+        <htailarm unit="FT"> 15.7 </htailarm>
+        <vtailarea unit="FT2"> 16.5 </vtailarea>
+        <vtailarm unit="FT"> 0 </vtailarm>
+        <location name="AERORP" unit="IN">
+            <x> 43.2 </x>
+            <y> 0 </y>
+            <z> 59.4 </z>
+        </location>
+        <location name="EYEPOINT" unit="IN">
+            <x> 37 </x>
+            <y> 0 </y>
+            <z> 48 </z>
+        </location>
+        <location name="VRP" unit="IN">
+            <x> 42.6 </x>
+            <y> 0 </y>
+            <z> 38.5 </z>
+        </location>
+    </metrics>
+
+    <mass_balance>
+        <ixx unit="SLUG*FT2"> 948 </ixx>
+        <iyy unit="SLUG*FT2"> 1346 </iyy>
+        <izz unit="SLUG*FT2"> 1967 </izz>
+        <ixy unit="SLUG*FT2"> -0 </ixy>
+        <ixz unit="SLUG*FT2"> -0 </ixz>
+        <iyz unit="SLUG*FT2"> -0 </iyz>
+        <emptywt unit="LBS"> 1500 </emptywt>
+        <location name="CG" unit="IN">
+            <x> 41 </x>
+            <y> 0 </y>
+            <z> 36.5 </z>
+        </location>
+        <pointmass name="name">
+            <weight unit="LBS"> 180 </weight>
+            <location name="POINTMASS" unit="IN">
+                <x> 36 </x>
+                <y> -14 </y>
+                <z> 24 </z>
+            </location>
+        </pointmass>
+    </mass_balance>
+
+    <ground_reactions>
+        <contact type="BOGEY" name="NOSE">
+            <location unit="IN">
+                <x> -6.8 </x>
+                <y> 0 </y>
+                <z> -20 </z>
+            </location>
+            <static_friction> 0.8 </static_friction>
+            <dynamic_friction> 0.5 </dynamic_friction>
+            <rolling_friction> 0.02 </rolling_friction>
+            <spring_coeff unit="LBS/FT"> 1800 </spring_coeff>
+            <damping_coeff unit="LBS/FT/SEC"> 600 </damping_coeff>
+            <max_steer unit="DEG"> 10 </max_steer>
+            <brake_group> NONE </brake_group>
+            <retractable>0</retractable>
+        </contact>
+        <contact type="BOGEY" name="LEFT_MAIN">
+            <location unit="IN">
+                <x> 58.2 </x>
+                <y> -43 </y>
+                <z> -17.9 </z>
+            </location>
+            <static_friction> 0.8 </static_friction>
+            <dynamic_friction> 0.5 </dynamic_friction>
+            <rolling_friction> 0.02 </rolling_friction>
+            <spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
+            <damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
+            <max_steer unit="DEG"> 0.0 </max_steer>
+            <brake_group> LEFT </brake_group>
+            <retractable>0</retractable>
+        </contact>
+        <contact type="BOGEY" name="RIGHT_MAIN">
+            <location unit="IN">
+                <x> 58.2 </x>
+                <y> 43 </y>
+                <z> -17.9 </z>
+            </location>
+            <static_friction> 0.8 </static_friction>
+            <dynamic_friction> 0.5 </dynamic_friction>
+            <rolling_friction> 0.02 </rolling_friction>
+            <spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
+            <damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
+            <max_steer unit="DEG"> 0.0 </max_steer>
+            <brake_group> RIGHT </brake_group>
+            <retractable>0</retractable>
+        </contact>
+        <contact type="BOGEY" name="TAIL_SKID">
+            <location unit="IN">
+                <x> 188 </x>
+                <y> 0 </y>
+                <z> 8 </z>
+            </location>
+            <static_friction> 0.2 </static_friction>
+            <dynamic_friction> 0.2 </dynamic_friction>
+            <rolling_friction> 0.2 </rolling_friction>
+            <spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
+            <damping_coeff unit="LBS/FT/SEC"> 1000 </damping_coeff>
+            <max_steer unit="DEG"> 0.0 </max_steer>
+            <brake_group> NONE </brake_group>
+            <retractable>0</retractable>
+        </contact>
+        <contact type="BOGEY" name="LEFT_TIP">
+            <location unit="IN">
+                <x> 43.2 </x>
+                <y> -214.8 </y>
+                <z> 59.4 </z>
+            </location>
+            <static_friction> 0.2 </static_friction>
+            <dynamic_friction> 0.2 </dynamic_friction>
+            <rolling_friction> 0.2 </rolling_friction>
+            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
+            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
+            <max_steer unit="DEG"> 0.0 </max_steer>
+            <brake_group> NONE </brake_group>
+            <retractable>0</retractable>
+        </contact>
+        <contact type="BOGEY" name="RIGHT_TIP">
+            <location unit="IN">
+                <x> 43.2 </x>
+                <y> 214.8 </y>
+                <z> 59.4 </z>
+            </location>
+            <static_friction> 0.2 </static_friction>
+            <dynamic_friction> 0.2 </dynamic_friction>
+            <rolling_friction> 0.2 </rolling_friction>
+            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
+            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
+            <max_steer unit="DEG"> 0.0 </max_steer>
+            <brake_group> NONE </brake_group>
+            <retractable>0</retractable>
+        </contact>
+    </ground_reactions>
+    <propulsion>
+        <engine file="eng_io320">
+            <location unit="IN">
+                <x> -19.7 </x>
+                <y> 0 </y>
+                <z> 26.6 </z>
+            </location>
+            <orient unit="DEG">
+                <roll> 0.0 </roll>
+                <pitch> 0 </pitch>
+                <yaw> 0 </yaw>
+            </orient>
+            <feed>0</feed>
+            <feed>1</feed>
+            <thruster file="prop_75in2f">
+                <location unit="IN">
+                    <x> -37.7 </x>
+                    <y> 0 </y>
+                    <z> 26.6 </z>
+                </location>
+                <orient unit="DEG">
+                    <roll> 0.0 </roll>
+                    <pitch> 0.0 </pitch>
+                    <yaw> 0.0 </yaw>
+                </orient>
+                <sense> 1 </sense>
+                <p_factor> 10 </p_factor>
+            </thruster>
+        </engine>
+        <tank type="FUEL">    <!-- Tank number 0 -->
+            <location unit="IN">
+                <x> 56 </x>
+                <y> -112 </y>
+                <z> 59.4 </z>
+            </location>
+            <capacity unit="LBS"> 185 </capacity>
+            <contents unit="LBS"> 100 </contents>
+        </tank>
+        <tank type="FUEL">    <!-- Tank number 1 -->
+            <location unit="IN">
+                <x> 56 </x>
+                <y> 112 </y>
+                <z> 59.4 </z>
+            </location>
+            <capacity unit="LBS"> 185 </capacity>
+            <contents unit="LBS"> 100 </contents>
+        </tank>
+    </propulsion>
+    <flight_control name="FCS: c172">
+        <channel name="Pitch">
+            <summer name="Pitch Trim Sum">
+                <input>fcs/elevator-cmd-norm</input>
+                <input>fcs/pitch-trim-cmd-norm</input>
+                <clipto>
+                    <min>-1</min>
+                    <max>1</max>
+                </clipto>
+            </summer>
+
+            <aerosurface_scale name="Elevator Control">
+                <input>fcs/pitch-trim-sum</input>
+                <gain>0.01745</gain>
+                <range>
+                    <min>-28</min>
+                    <max>23</max>
+                </range>
+                <output>fcs/elevator-pos-rad</output>
+            </aerosurface_scale>
+        </channel>
+        <channel name="Roll">
+            <summer name="Roll Trim Sum">
+                <input>fcs/aileron-cmd-norm</input>
+                <input>fcs/roll-trim-cmd-norm</input>
+                <clipto>
+                    <min>-1</min>
+                    <max>1</max>
+                </clipto>
+            </summer>
+
+            <aerosurface_scale name="Left Aileron Control">
+                <input>fcs/roll-trim-sum</input>
+                <gain>0.01745</gain>
+                <range>
+                    <min>-20</min>
+                    <max>15</max>
+                </range>
+                <output>fcs/left-aileron-pos-rad</output>
+            </aerosurface_scale>
+
+            <aerosurface_scale name="Right Aileron Control">
+                <input>fcs/roll-trim-sum</input>
+                <gain>-0.01745</gain>
+                <range>
+                    <min>-20</min>
+                    <max>15</max>
+                </range>
+                <output>fcs/right-aileron-pos-rad</output>
+            </aerosurface_scale>
+        </channel>
+        <channel name="Yaw">
+            <summer name="Yaw Trim Sum">
+                <input>fcs/rudder-cmd-norm</input>
+                <input>fcs/yaw-trim-cmd-norm</input>
+                <clipto>
+                    <min>-1</min>
+                    <max>1</max>
+                </clipto>
+            </summer>
+
+            <aerosurface_scale name="Rudder Control">
+                <input>fcs/yaw-trim-sum</input>
+                <gain>0.01745</gain>
+                <range>
+                    <min>-16</min>
+                    <max>16</max>
+                </range>
+                <output>fcs/rudder-pos-rad</output>
+            </aerosurface_scale>
+        </channel>
+        <channel name="Flaps">
+            <kinematic name="Flaps Control">
+                <input>fcs/flap-cmd-norm</input>
+                <traverse>
+                    <setting>
+                        <position>0</position>
+                        <time>0</time>
+                    </setting>
+                    <setting>
+                        <position>10</position>
+                        <time>2</time>
+                    </setting>
+                    <setting>
+                        <position>20</position>
+                        <time>1</time>
+                    </setting>
+                    <setting>
+                        <position>30</position>
+                        <time>1</time>
+                    </setting>
+                </traverse>
+                <output>fcs/flap-pos-deg</output>
+            </kinematic>
+        </channel>
+    </flight_control>
+    <aerodynamics>
+
+        <function name="aero/function/kCDge">
+            <description>Change_in_drag_due_to_ground_effect</description>
+            <product>
+                  <table>
+                      <independentVar>aero/h_b-mac-ft</independentVar>
+                      <tableData>
+                          0.0000	0.0480
+                          0.1000	0.5150
+                          0.1500	0.6290
+                          0.2000	0.7090
+                          0.3000	0.8150
+                          0.4000	0.8820
+                          0.5000	0.9280
+                          0.6000	0.9620
+                          0.7000	0.9880
+                          0.8000	1.0000
+                          0.9000	1.0000
+                          1.0000	1.0000
+                          1.1000	1.0000
+                      </tableData>
+                  </table>
+            </product>
+        </function>
+
+        <function name="aero/function/kCLge">
+            <description>Change_in_lift_due_to_ground_effect</description>
+            <product>
+                  <table>
+                      <independentVar>aero/h_b-mac-ft</independentVar>
+                      <tableData>
+                          0.0000	1.2030
+                          0.1000	1.1270
+                          0.1500	1.0900
+                          0.2000	1.0730
+                          0.3000	1.0460
+                          0.4000	1.0550
+                          0.5000	1.0190
+                          0.6000	1.0130
+                          0.7000	1.0080
+                          0.8000	1.0060
+                          0.9000	1.0030
+                          1.0000	1.0020
+                          1.1000	1.0000
+                      </tableData>
+                  </table>
+            </product>
+        </function>
+
+        <axis name="DRAG">
+            <function name="aero/coefficient/CDo">
+                <description>Drag_at_zero_lift</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <value>0.027</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/CDDf">
+                <description>Delta_drag_due_to_flap_deflection</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>aero/function/kCDge</property>
+                      <table>
+                          <independentVar>fcs/flap-pos-deg</independentVar>
+                          <tableData>
+                              0.0000	0.0000
+                              10.0000	0.0070
+                              20.0000	0.0120
+                              30.0000	0.0180
+                          </tableData>
+                      </table>
+                </product>
+            </function>
+            <function name="aero/coefficient/CDwbh">
+                <description>Drag_due_to_alpha</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>aero/function/kCDge</property>
+                      <table>
+                          <independentVar lookup="row">aero/alpha-rad</independentVar>
+                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
+                          <tableData>
+                                0.0000	10.0000	20.0000	30.0000
+                              -0.0873	0.0041	0.0000	0.0005	0.0014
+                              -0.0698	0.0013	0.0004	0.0025	0.0041
+                              -0.0524	0.0001	0.0023	0.0059	0.0084
+                              -0.0349	0.0003	0.0057	0.0108	0.0141
+                              -0.0175	0.0020	0.0105	0.0172	0.0212
+                              0.0000	0.0052	0.0168	0.0251	0.0299
+                              0.0175	0.0099	0.0248	0.0346	0.0402
+                              0.0349	0.0162	0.0342	0.0457	0.0521
+                              0.0524	0.0240	0.0452	0.0583	0.0655
+                              0.0698	0.0334	0.0577	0.0724	0.0804
+                              0.0873	0.0442	0.0718	0.0881	0.0968
+                              0.1047	0.0566	0.0874	0.1053	0.1148
+                              0.1222	0.0706	0.1045	0.1240	0.1343
+                              0.1396	0.0860	0.1232	0.1442	0.1554
+                              0.1571	0.0962	0.1353	0.1573	0.1690
+                              0.1745	0.1069	0.1479	0.1708	0.1830
+                              0.1920	0.1180	0.1610	0.1849	0.1975
+                              0.2094	0.1298	0.1746	0.1995	0.2126
+                              0.2269	0.1424	0.1892	0.2151	0.2286
+                              0.2443	0.1565	0.2054	0.2323	0.2464
+                              0.2618	0.1727	0.2240	0.2521	0.2667
+                              0.2793	0.1782	0.2302	0.2587	0.2735
+                              0.2967	0.1716	0.2227	0.2507	0.2653
+                              0.3142	0.1618	0.2115	0.2388	0.2531
+                              0.3316	0.1475	0.1951	0.2214	0.2351
+                              0.3491	0.1097	0.1512	0.1744	0.1866
+                          </tableData>
+                      </table>
+                </product>
+            </function>
+            <function name="aero/coefficient/CDDe">
+                <description>Drag_due_to_Elevator_Deflection</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>fcs/mag-elevator-pos-rad</property>
+                    <value>0.0000</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/CDbeta">
+                <description>Drag_due_to_sideslip</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>aero/mag-beta-rad</property>
+                    <value>0.1700</value>
+                </product>
+            </function>
+        </axis>
+
+        <axis name="SIDE">
+            <function name="aero/coefficient/CYb">
+                <description>Side_force_due_to_beta</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                      <table>
+                          <independentVar lookup="row">aero/beta-rad</independentVar>
+                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
+                          <tableData>
+                                0.0000	30.0000
+                              -0.3490	0.1370	0.1060
+                              0.0000	0.0000	0.0000
+                              0.3490	-0.1370	-0.1060
+                          </tableData>
+                      </table>
+                </product>
+            </function>
+            <function name="aero/coefficient/CYda">
+                <description>Side_force_due_to_aileron</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>fcs/left-aileron-pos-rad</property>
+                    <value>0.0000</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/CYdr">
+                <description>Side_force_due_to_rudder</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>fcs/rudder-pos-rad</property>
+                    <value>0.1870</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/CYp">
+                <description>Side_force_due_to_roll_rate</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>aero/bi2vel</property>
+                    <property>velocities/p-aero-rad_sec</property>
+                      <table>
+                          <independentVar lookup="row">aero/alpha-rad</independentVar>
+                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
+                          <tableData>
+                                0.0000	30.0000
+                              0.0000	-0.0750	-0.1610
+                              0.0940	-0.1450	-0.2310
+                          </tableData>
+                      </table>
+                </product>
+            </function>
+            <function name="aero/coefficient/CYr">
+                <description>Side_force_due_to_yaw_rate</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>aero/bi2vel</property>
+                    <property>velocities/r-aero-rad_sec</property>
+                      <table>
+                          <independentVar lookup="row">aero/alpha-rad</independentVar>
+                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
+                          <tableData>
+                                0.0000	30.0000
+                              0.0000	0.2140	0.1620
+                              0.0940	0.2670	0.2150
+                          </tableData>
+                      </table>
+                </product>
+            </function>
+        </axis>
+
+        <axis name="LIFT">
+            <function name="aero/coefficient/CLwbh">
+                <description>Lift_due_to_alpha</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>aero/function/kCLge</property>
+                      <table>
+                          <independentVar lookup="row">aero/alpha-rad</independentVar>
+                          <independentVar lookup="column">aero/stall-hyst-norm</independentVar>
+                          <tableData>
+                                0.0000	1.0000
+                              -0.0900	-0.2200	-0.2200
+                              0.0000	0.2500	0.2500
+                              0.0900	0.7300	0.7300
+                              0.1000	0.8300	0.7800
+                              0.1200	0.9200	0.7900
+                              0.1400	1.0200	0.8100
+                              0.1600	1.0800	0.8200
+                              0.1700	1.1300	0.8300
+                              0.1900	1.1900	0.8500
+                              0.2100	1.2500	0.8600
+                              0.2400	1.3500	0.8800
+                              0.2600	1.4400	0.9000
+                              0.2800	1.4700	0.9200
+                              0.3000	1.4300	0.9500
+                              0.3200	1.3800	0.9900
+                              0.3400	1.3000	1.0500
+                              0.3600	1.1500	1.1500
+                          </tableData>
+                      </table>
+                </product>
+            </function>
+            <function name="aero/coefficient/CLDf">
+                <description>Delta_lift_due_to_flap_deflection</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>aero/function/kCLge</property>
+                      <table>
+                          <independentVar>fcs/flap-pos-deg</independentVar>
+                          <tableData>
+                              0.0000	0.0000
+                              10.0000	0.2000
+                              20.0000	0.3000
+                              30.0000	0.3500
+                          </tableData>
+                      </table>
+                </product>
+            </function>
+            <function name="aero/coefficient/CLDe">
+                <description>Lift_due_to_Elevator_Deflection</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>fcs/elevator-pos-rad</property>
+                    <value>0.4300</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/CLadot">
+                <description>Lift_due_to_alpha_rate</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>aero/alphadot-rad_sec</property>
+                    <property>aero/ci2vel</property>
+                    <value>1.7000</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/CLq">
+                <description>Lift_due_to_pitch_rate</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>velocities/q-aero-rad_sec</property>
+                    <property>aero/ci2vel</property>
+                    <value>3.9000</value>
+                </product>
+            </function>
+        </axis>
+
+        <axis name="ROLL">
+            <function name="aero/coefficient/Clb">
+                <description>Roll_moment_due_to_beta</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/bw-ft</property>
+                      <table>
+                          <independentVar>aero/beta-rad</independentVar>
+                          <tableData>
+                              -0.3490	0.0322
+                              0.0000	0.0000
+                              0.3490	-0.0322
+                          </tableData>
+                      </table>
+                </product>
+            </function>
+            <function name="aero/coefficient/Clp">
+                <description>Roll_moment_due_to_roll_rate_(roll_damping)</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/bw-ft</property>
+                    <property>aero/bi2vel</property>
+                    <property>velocities/p-aero-rad_sec</property>
+                    <value>-0.4840</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/Clr">
+                <description>Roll_moment_due_to_yaw_rate</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/bw-ft</property>
+                    <property>aero/bi2vel</property>
+                    <property>velocities/r-aero-rad_sec</property>
+                      <table>
+                          <independentVar lookup="row">aero/alpha-rad</independentVar>
+                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
+                          <tableData>
+                                0.0000	30.0000
+                              0.0000	0.0798	0.1246
+                              0.0940	0.1869	0.2317
+                          </tableData>
+                      </table>
+                </product>
+            </function>
+            <function name="aero/coefficient/ClDa">
+                <description>Roll_moment_due_to_aileron</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/bw-ft</property>
+                    <property>fcs/left-aileron-pos-rad</property>
+                    <value>0.2290</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/Cldr">
+                <description>Roll_moment_due_to_rudder</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/bw-ft</property>
+                    <property>fcs/rudder-pos-rad</property>
+                    <value>0.0147</value>
+                </product>
+            </function>
+        </axis>
+
+        <axis name="PITCH">
+            <function name="aero/coefficient/Cmo">
+                <description>Pitching_moment_at_zero_alpha</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/cbarw-ft</property>
+                    <value>0.1000</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/Cmalpha">
+                <description>Pitch_moment_due_to_alpha</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/cbarw-ft</property>
+                    <property>aero/alpha-rad</property>
+                    <value>-1.8000</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/Cmq">
+                <description>Pitch_moment_due_to_pitch_rate</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/cbarw-ft</property>
+                    <property>aero/ci2vel</property>
+                    <property>velocities/q-aero-rad_sec</property>
+                    <value>-12.4000</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/Cmadot">
+                <description>Pitch_moment_due_to_alpha_rate</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/cbarw-ft</property>
+                    <property>aero/ci2vel</property>
+                    <property>aero/alphadot-rad_sec</property>
+                    <value>-7.2700</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/Cmde">
+                <description>Pitch_moment_due_to_elevator_deflection</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/cbarw-ft</property>
+                    <property>fcs/elevator-pos-rad</property>
+                    <value>-1.1220</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/Cmdf">
+                <description>Delta_pitching_moment_due_to_flap_deflection</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/cbarw-ft</property>
+                      <table>
+                          <independentVar>fcs/flap-pos-deg</independentVar>
+                          <tableData>
+                              0.0000	0.0000
+                              10.0000	-0.0654
+                              20.0000	-0.0981
+                              30.0000	-0.1140
+                          </tableData>
+                      </table>
+                </product>
+            </function>
+        </axis>
+
+        <axis name="YAW">
+            <function name="aero/coefficient/Cnb">
+                <description>Yaw_moment_due_to_beta</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/bw-ft</property>
+                      <table>
+                          <independentVar>aero/beta-rad</independentVar>
+                          <tableData>
+                              -0.3490	-0.0205
+                              0.0000	0.0000
+                              0.3490	0.0205
+                          </tableData>
+                      </table>
+                </product>
+            </function>
+            <function name="aero/coefficient/Cnp">
+                <description>Yaw_moment_due_to_roll_rate</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/bw-ft</property>
+                    <property>aero/bi2vel</property>
+                    <property>velocities/p-aero-rad_sec</property>
+                    <value>-0.0278</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/Cnr">
+                <description>Yaw_moment_due_to_yaw_rate</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/bw-ft</property>
+                    <property>aero/bi2vel</property>
+                    <property>velocities/r-aero-rad_sec</property>
+                    <value>-0.0937</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/Cnda">
+                <description>Yaw_moment_due_to_aileron</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/bw-ft</property>
+                    <property>fcs/left-aileron-pos-rad</property>
+                    <value>-0.0053</value>
+                </product>
+            </function>
+            <function name="aero/coefficient/Cndr">
+                <description>Yaw_moment_due_to_rudder</description>
+                <product>
+                    <property>aero/qbar-psf</property>
+                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/bw-ft</property>
+                    <property>fcs/rudder-pos-rad</property>
+                    <value>-0.0430</value>
+                </product>
+            </function>
+        </axis>
+    </aerodynamics>
+</fdm_config>