<FDM_CONFIG NAME="f15" VERSION="1.60">

<!--
  File:        f15.xml
  Author:      Erik Hofman
  CVS Version: $Id: f15.xml,v 1.1 2002/11/23 16:06:30 tony Exp $

  Function: Models an F-15 "Eagle"
  Status:   Beta

  Sources:
    Dryden Technical Reports Server documents:
        H-823:  Initial results from flight testing a large, remotely piloted
                airplane model.
        H-905:  Subsonic stability and control deratives for an unpowered,
                remotely piloted 3/8-scale F-15 airplane model obtained
                from flight test.
	H-1990:	Evaluating the dynamic response of in-flight thrust calculation
                techniques during throttle transients.
        H-1999:	Dynamic ground effects flight test of an F-15 aircraft.

  
  Maximum lift:		1.2
  AOA for zero lift:	-2 degrees
  Maximum AOA:		31.3 degrees

  Pitch rate damper:	0.4 deg/deg/sec
  Roll damper gain:	0.8 deg/deg/sec
  Yaw damper gain:	1.0 deg/deg/sec
  Yaw rate washout:	1.86 seconds
-->

  <METRICS>

    AC_WINGAREA 608.0
    AC_WINGSPAN  42.83
    AC_CHORD     15.95
    AC_HTAILAREA 45.01
    AC_HTAILARM  20.0
    AC_VTAILAREA 46.96
    AC_LV        20.0
    AC_IXX      22000
    AC_IYY     182000
    AC_IZZ     200000
    AC_IXZ       1230
    AC_EMPTYWT  30035
    AC_AERORP    223.89   0.0   13.2
    AC_CGLOC     221.65   0.0    4.1
    AC_EYEPTLOC  447.0    0.0   45.0
    AC_POINTMASS 230.0  447.0    0.0   36.0

  </METRICS>

  <UNDERCARRIAGE>

     AC_GEAR  NOSE      408.4    0.0 -77.5  2500  800 0.5 0.8 0.02 STEERABLE NOSE 20 RETRACT
     AC_GEAR  MLG_LEFT  195.0  -54.0 -77.5  5400 1600 0.5 0.8 0.02 FIXED     LEFT  0 RETRACT
     AC_GEAR  MLG_RIGHT 195.0   54.0 -77.5  5400 1600 0.5 0.8 0.02 FIXED     RIGHT 0 RETRACT

     AC_GEAR  WT_LEFT   128.5 -257.0   0.0 10000 2000 0.2 0.2 0.2  FIXED     NONE  0 FIXED
     AC_GEAR  WT_RIGHT  128.5  257.0   0.0 10000 2000 0.2 0.2 0.2  FIXED     NONE  0 FIXED
     AC_GEAR  VT_LEFT     0.0  -57.0 131.0 10000 2000 0.2 0.2 0.2  FIXED     NONE  0 FIXED
     AC_GEAR  VT_RIGHT    0.0   57.0 131.0 10000 2000 0.2 0.2 0.2  FIXED     NONE  0 FIXED
     AC_GEAR  RADOME    664.4    0.0 -19.5 10000 2000 0.2 0.2 0.2  FIXED     NONE  0 FIXED
     AC_GEAR  BELLY     128.5    0.0 -46.5 10000 2000 0.2 0.2 0.2  FIXED     NONE  0 FIXED

  </UNDERCARRIAGE>

  <PROPULSION>

    <AC_ENGINE FILE="low_bypass_turbofan">
      XLOC       0.0
      YLOC     -25.5
      ZLOC       0.0
      PITCH      0.0
      YAW        0.0
      FEED         0
      FEED         1
    </AC_ENGINE>

    <AC_ENGINE FILE="low_bypass_turbofan">
      XLOC       0.0
      YLOC      25.5
      ZLOC       0.0
      PITCH      0.0
      YAW        0.0
      FEED         0
      FEED         1
    </AC_ENGINE>

    <AC_THRUSTER FILE="direct">
      XLOC       0.0
      YLOC     -25.5
      ZLOC       0.0
      PITCH      0.0
      YAW        0
    </AC_THRUSTER>

    <AC_THRUSTER FILE="direct">
      XLOC       0.0
      YLOC      25.5
      ZLOC       0.0
      PITCH      0.0
      YAW        0
    </AC_THRUSTER>

    <AC_TANK TYPE="FUEL" NUMBER="0">
      XLOC     195.0
      YLOC    -108.0
      ZLOC       0.0
      RADIUS    29.4
      CAPACITY 185.0
      CONTENTS 100.0
    </AC_TANK>

    <AC_TANK TYPE="FUEL" NUMBER="1">
      XLOC     195.0
      YLOC     108.0
      ZLOC       0.0
      RADIUS     0.0
      CAPACITY 185.0
      CONTENTS 100.0
    </AC_TANK>

  </PROPULSION>


  <FLIGHT_CONTROL NAME="f15">

    <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          -26
       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="Left 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="Right Aileron Control" TYPE="AEROSURFACE_SCALE">
       INPUT         fcs/roll-trim-sum
       MIN          -20
       MAX           20
       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         -30
       MAX          30
       GAIN         0.01745
       OUTPUT       fcs/rudder-pos-rad
     </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 -0.349 0.873

     <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   1.061
            0.1   1.033
            0.15  1.031
            0.2   1.033
            0.3   1.028
            0.4   1.011
            0.5   1.009
            0.6   1.005
            0.7   1.002
            0.8   1.000
            0.9   1.000
            1.0   1.000
            1.1   1.000
         </FACTOR>
         <!--
              CL is accurate for alpha of 0 ... 0.558, the rest is an estimate
              based on the fact that CL=0 for alpha=-0.0349 and CLmax = 1.2
           -->
         <COEFFICIENT NAME="CLalpha" TYPE="VECTOR">
           Lift_due_to_alpha
           16
           aero/alpha-rad
           aero/qbar-psf | metrics/Sw-sqft
           -0.349	-0.93
           -0.262	-0.86
           -0.175	-0.58
           -0.087	-0.26
           0.000	0.06
           0.070	0.30
           0.140	0.58
           0.209	0.78
           0.279	0.88
           0.349	1.01
           0.419	1.08
           0.489	1.16
           0.559	1.19
           0.698	1.01
           0.785	0.93
           0.873	0.81
         </COEFFICIENT>
       </GROUP>

       <COEFFICIENT NAME="CLDe" TYPE="VALUE">
         Lift_due_to_Elevator_Deflection
         aero/qbar-psf | metrics/Sw-sqft | fcs/elevator-pos-rad | aero/beta-rad
         0.0
       </COEFFICIENT>

    </AXIS>

    <AXIS NAME="DRAG">

       <GROUP NAME="CDb">
         Basic_drag
         <FACTOR NAME="kCDge" TYPE="VECTOR">
            Change_in_drag_due_to_ground_effect
            13
            aero/h_b-mac-ft
            none
            0.0   0.81
            0.1   0.99
            0.15  0.95
            0.2   0.98
            0.3   0.99
            0.4   1.00
            0.5   1.04
            0.6   1.01
            0.7   0.99
            0.8   1.01
            0.9   1.00
            1.0   1.00
            1.1   1.00
         </FACTOR>
         <!--
              CDmin is calculated from flight test date as described in H-1990
              as a function of Fex, FNP, W, y, v, S and rho
           -->
         <COEFFICIENT NAME="CDmin" TYPE="VALUE">
           Drag_minimum
           aero/qbar-psf | metrics/Sw-sqft
           0.00474
         </COEFFICIENT>
         <!--
              CDalpha is calculated based on CL and CNb and therefore is accurate
              for alpha of 0 ... 0.558
           -->
         <COEFFICIENT NAME="CDalpha" TYPE="VECTOR">
           Drag_due_to_alpha
           16
           aero/alpha-rad
           aero/qbar-psf | metrics/Sw-sqft | aero/mag-beta-rad
           -0.349	2.5954
           -0.262	3.2686
           -0.175	3.3563
           -0.087	3.0533
           0.000	3.8228
           0.070	4.3450
           0.140	4.1909
           0.209	3.7331
           0.279	3.1268
           0.349	2.8246
           0.419	2.4657
           0.489	2.2127
           0.559	1.9317
           0.698	1.2283
           0.785	0.9522
           0.873	0.7015
        </COEFFICIENT>
      </GROUP>

      <COEFFICIENT NAME="CDDe" TYPE="VALUE">
        Drag_due_to_Elevator_Deflection
        aero/qbar-psf | metrics/Sw-sqft | fcs/mag-elevator-pos-rad
        0.0
      </COEFFICIENT>

    </AXIS>

    <AXIS NAME="SIDE">

       <COEFFICIENT NAME="CYb" TYPE="VECTOR">
         Side_force_due_to_beta
         4
         aero/alpha-rad
         aero/qbar-psf | metrics/Sw-sqft | aero/beta-rad
         -0.349	-0.8594
          0.070	-0.0974
          0.559	-0.0115
          0.873	-0.3552
       </COEFFICIENT>

       <COEFFICIENT NAME="CYda" TYPE="VALUE">
         Side_force_due_to_aileron
         aero/qbar-psf | metrics/Sw-sqft | fcs/left-aileron-pos-rad
         0.00
      </COEFFICIENT>

      <COEFFICIENT NAME="CYdr" TYPE="VALUE">
         Side_force_due_to_rudder
         aero/qbar-psf | metrics/Sw-sqft | fcs/rudder-pos-rad
         0.37242
      </COEFFICIENT>

    </AXIS>

    <AXIS NAME="ROLL">

       <COEFFICIENT NAME="Clb" TYPE="VECTOR">
         Roll_moment_due_to_beta
         9
         aero/alpha-rad
         aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/beta-rad
         -0.349	0.0286
         -0.175	-0.2292
         0.000	-0.0573
         0.209	-0.1719
         0.314	-0.1146
         0.419	-0.1719
         0.698	-0.0745
         0.785	-0.1146
         0.873	-0.1203
       </COEFFICIENT>

       <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
         -0.31
       </COEFFICIENT>

       <COEFFICIENT NAME="Clr" TYPE="VALUE">
         Roll_moment_due_to_yaw_rate
         aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/r-aero-rad_sec
         0.0001
       </COEFFICIENT>

       <COEFFICIENT NAME="ClDa" TYPE="VECTOR">
         Roll_moment_due_to_aileron
         5
         aero/alpha-rad
         aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
         -0.349	0.0172
         -0.087	0.0372
         0.140	0.0401
         0.559	0.0057
         0.873	0.0057
       </COEFFICIENT>

       <COEFFICIENT NAME="ClDr" TYPE="VALUE">
         Roll_moment_due_to_rudder
         aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
         0.01146
        </COEFFICIENT>

      </AXIS>

    <AXIS NAME="PITCH">

      <GROUP NAME="Cmb">
        Basic_pitch
        <FACTOR NAME="kCmge" TYPE="VECTOR">
           Change_in_pitch_due_to_ground_effect
           13
           aero/h_b-mac-ft
           none
           0.0   0.992
           0.1   0.996
           0.15  0.999
           0.2   0.997
           0.3   1.000
           0.4   1.000
           0.5   1.002
           0.6   1.001
           0.7   0.998
           0.8   0.999
           0.9   1.000
           1.0   1.000
           1.1   1.000
        </FACTOR>
        <COEFFICIENT NAME="Cmalpha" TYPE="VECTOR">
          Pitch_moment_due_to_alpha
          8
          aero/alpha-rad
          aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/alpha-rad
          -0.349	-1.1459
          -0.262	-0.5730
          -0.131	-0.0573
          0.000		-0.2292
          0.279		-0.5157
          0.419		-0.8594
          0.559		-0.4584
          0.873		-0.5157
        </COEFFICIENT>
      </GROUP>

      <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
         -4.7
      </COEFFICIENT>

      <COEFFICIENT NAME="Cmde" TYPE="VALUE">
        Pitch_moment_due_to_elevator_deflection
        aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | fcs/elevator-pos-rad
        -0.458
      </COEFFICIENT>

    </AXIS>

    <AXIS NAME="YAW">

       <COEFFICIENT NAME="Cnb" TYPE="VECTOR">
         Yaw_moment_due_to_beta
         5
         aero/alpha-rad
         aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/beta-rad
         -0.349	0.0745
         0.000	0.1776
         0.349	0.0057
         0.524	-0.0974
         0.873	-0.0286
       </COEFFICIENT>

       <COEFFICIENT NAME="Cnp" TYPE="VECTOR">
         Yaw_moment_due_to_roll_rate
         6
         aero/alpha-rad
         aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/p-aero-rad_sec
         -0.349	0.11
         -0.087	-0.14
         0.000	-0.10
         0.279	0.01
         0.419	-0.13
         0.873	-0.18
        </COEFFICIENT>

       <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
         -0.3
       </COEFFICIENT>

       <COEFFICIENT NAME="Cnda" TYPE="VALUE">
         Yaw_moment_due_to_aileron
         aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
         0.0573
       </COEFFICIENT>

       <COEFFICIENT NAME="Cndr" TYPE="VECTOR">
         Yaw_moment_due_to_rudder
         2
         aero/alpha-rad
         aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
         -0.349	-0.06875
         0.873	-0.01146
       </COEFFICIENT>

    </AXIS>
  </AERODYNAMICS>
  <OUTPUT NAME="JSBout.csv" TYPE="NONE">
    RATE_IN_HZ       20
    SIMULATION       OFF
    ATMOSPHERE       ON
    MASSPROPS        OFF
    AEROSURFACES     OFF
    RATES            OFF
    VELOCITIES       OFF
    FORCES           OFF
    MOMENTS          OFF
    POSITION         OFF
    COEFFICIENTS     OFF
    GROUND_REACTIONS OFF
    FCS              OFF
    PROPULSION       OFF
  </OUTPUT>
</FDM_CONFIG>

