<?xml version="1.0"?>
<?xml-stylesheet href="http://jsbsim.sourceforge.net/JSBSim.xsl" type="text/xsl"?>
<fdm_config name="F-8E-Crusader" version="2.0" release="BETA"
 xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
 xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">


    <fileheader>
        <author>from template (Aeromatic), Gérard Robin, and Alva </author>
        <filecreationdate>17-October-2010</filecreationdate>
        <version> Version 1.4 better data from Naca Doc</version>
        <description> Models a F-8E-Crusader </description>
        <note>
            This model was created using publicly available data, publicly available
            technical reports, textbooks, and guesses. It contains no proprietary or
            restricted data. It has been validated only to the extent that it seems
            to "fly right", and possibly to comply to published, publicly known,
            performance data (maximum speed, endurance, etc.). Thus, this model
            is meant for educational and entertainment purposes only.

            This simulation model is not endorsed by the manufacturer.
        </note>
	<documentation>

		http://aeronavale.free.fr/avion_crusader.htm
		*********************************************************************
		Vought F-8E (FN) Crusader : Caractéristiques principales
		Constructeur     Ling-Temco-Vought
		Mission     Interception tout temps
		Envergure     10.72 m
		Longueur     16.61 m
		Hauteur     4.80 m
		Surface alaire     34.84 m2
		Poids max 	    13 000 kg
		Moteur     1 réacteur J 57 P 20 A Pratt et Whitney
		Vitesse max    Mach 1.8
		Vitesse de croisière     860 km/h
		Vitesse d'appontage     180 km/h (97kt)
		Plafond     50.000 pieds
		Distance franchissable     1 500 nautiques
		Autonomie     2 h 30
		********************************************************************************
		http://www.vought.com/heritage/products/html/f8u-2spec.html

		Data below for F-8C
		Dimensions
		Wingspan    35.17 ft
		Overall Langth    55.25 ft
		Height    15.75 ft
		Weights and Capacities
		Empty Weight    18950 lb
		Fuel Capacity    1348 gal

		Powerplant Characteristics
		Type:  Pratt  Whitney J57-P16
		Rating Thrust    10700 lb
		Rating Thrust with afterburner
		16900 lb

		Performance
		Maximum Speed, Sea Level
		1105 mph

		**********************************************************************
		http://www.aerospaceweb.org/aircraft/fighter/f8/

		Data below for F-8P
		Last modified 14 November 2004
		HISTORY:
		First Flight 	(XF-8U-1) 25 March 1955
		(F-8A) 20 September 1955
		Service Entry 	March 1957
		Retirement 	4 December 1999
		AIRFOIL SECTIONS:
		Wing Root 	NACA 65A006 mod
		Wing Tip 	NACA 65A005 mod
		DIMENSIONS:
		Length 	54.50 ft (16.61 m)
		Wingspan 	35.17 ft (10.72 m)
		Height 	15.75 ft (4.80 m)
		Wing Area 	374 ft2 (34.84 m2)
		WEIGHTS:
		Empty 	19,700 lb (8,935 kg)
		Typical Load 	27,560 lb (12,500 kg)
		Max Takeoff 	34,000 lb (15,420 kg)
		Fuel Capacity 	internal: 5,300 L
		PROPULSION:
		Powerplant 	one Pratt  Whitney J57-P-20A afterburning turbojet
		Thrust 	18,000 lb (80.07 kN)
		PERFORMANCE:
		Max Level Speed 	at altitude: 1,225 mph (1,975 km/h) at 40,000 ft (12,190 m), Mach 1.86
		at sea level: unknown
		Initial Climb Rate 	21,000 ft (6,410 m) / min
		Service Ceiling 	unknown
		Range 	typical: 380 nm (710 km)
		ferry: 1,040 nm (1,930 km)
		g-Limits 	unknown
		ARMAMENT:
		Gun 	four 20-mm Colt cannons (84 to 144 rds ea)
		Stations 	four external hardpoints
		Air-to-Air Missile 	R.530, Matra 550 Magic, AIM-9 Sidewinder
		*************************************************************************************************************************
		The F-8A entered service in March of 1957.
		Length: 				55' 3"
		Height:				15' 9"
		Wingspan (spread)		35' 8"
		Wing area:				375 sq. ft.
		NACA 65A006 mod

			F-8E
		Empty Wt:					        	19,200
		Max Launch Wt:					34,100
		Max Trap Wt:						22,000
		Approach speed @max:				140 kts
		Stall, pwr. on/off					123/145 kts
		JP-5, internal-gal/lb:					1,348/9,100
		Engine: PW J-57-P....				16
		Thrust, MRT/CRT, #:				10,700/18,000
		Guns:								4-20mm, 500 rds
		Missiles:							4 Sidewinder
		Max Speed, IMN/mph**:				1.9/1,255
		Combat Radius, nm:				355
		Service Ceiling, MRT				40,000'

		*************************************************************************

		from http://en.wikipedia.org/wiki/F-8_Crusader
		# Dry thrust: 10,700 lbf (47.6 kN)
		# Thrust with afterburner: 18,000 lbf (80.1 kN)
		Airfoil: NACA 65A006 mod root, NACA 65A005 mod tip
		Zero-lift drag coefficient: 0.0133
		# Drag area: 5.0 ft² (0.46 m²)
		# Aspect ratio: 3.42

                quelques documents qui donnent des courbes19930087197_1993087197-naca65A006.pdf
		et 19930087933_1993087933-naca65A006.pdf

		**************************************************************************
                >>>>>>>The very first version ( right now, outdated) was :File:     f8e.xml
			Author:   template Aero-Matic v 8
			Adons from Gerard Robin     07-10-2005   (jj mm aa)
			with an original carrier landing patch (from Mathias Froëhlich)
		Inputs:
		name:          Vought F-8E Crusader
		type:          single-engine transonic/supersonic fighter
		max weight:    34100 lb
		wing span:     35.17232 ft
		length:        54.49741 ft
		wing area:     375.0526 sq-ft
		gear type:     tricycle
		retractable?:  yes
		# engines:     1
		engine type:   turbine
		engine layout: aft fuselage
		yaw damper?    yes
		Outputs:
		wing loading:  90.92 lb/sq-ft
		CL-alpha:      3.5 per radian
		CL-0:          0.08
		CL-max:        1
		CD-0:          0.021
		K:             0.09
                >>>>>>>>>>>>>>>>
		******************************************************************************
	</documentation>
    </fileheader>

    <metrics>
        <wingarea unit="FT2"> 375.05 </wingarea>
        <wingspan unit="FT"> 35.17 </wingspan>
        <wing_incidence unit="DEG">0.0</wing_incidence>
        <chord unit="FT"> 14.76 </chord>
        <htailarea unit="FT2"> 57 </htailarea>
        <htailarm unit="FT"> 20.8 </htailarm>
        <vtailarea unit="FT2"> 113 </vtailarea>  <!--7.5 m2 + 3m2 (fanon)-->
        <vtailarm unit="FT"> 20.4 </vtailarm>
        <location name="AERORP" unit="IN">
            <x> 63</x>
            <y> 0 </y>
            <z> 23 </z>
        </location>
        <location name="EYEPOINT" unit="IN">
            <x> 130.8 </x>
            <y> 0 </y>
            <z> 36 </z>
        </location>
        <location name="VRP" unit="IN">
            <x> 0 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
    </metrics>

    <mass_balance>
        <ixx unit="SLUG*FT2">     14326 </ixx>
        <iyy unit="SLUG*FT2">     61143 </iyy>
        <izz unit="SLUG*FT2">     56327 </izz>

       <!-- <ixx unit="SLUG*FT2"> 23803 </ixx>
        <iyy unit="SLUG*FT2"> 96049 </iyy>
        <izz unit="SLUG*FT2"> 84902 </izz>-->

        <emptywt unit="LBS"> 19700 </emptywt>
        <location name="CG" unit="IN">
            <x> 72</x>
            <y> 0 </y>
            <z> 0</z>
        </location>
        <pointmass name="Transfer-tank"> <!-- Tank Transfert  Max 5678 lbs -->
            <weight unit="LBS">4000</weight>
            <location name="Transfer Tank" unit="IN">
                <x> 72 </x>
                <y> 0 </y>
                <z> 17 </z>
            </location>
        </pointmass>
        <pointmass name="Main-tank">    <!-- Tank Main  Max 3488 lbs -->
            <weight unit="LBS">3000</weight>
            <location unit="IN">
                <x> 63 </x>
                <y> 0 </y>
                <z> 0 </z>
            </location>
        </pointmass>
        <pointmass name="Nose_Gear_Testing">
            <weight unit="LBS">0</weight>
            <location unit="IN">
                <x> -139.76 </x>
                <y> 0 </y>
                <z> -81.6 </z>
            </location>
        </pointmass>
        <pointmass name="Left_Gear_Testing">
            <weight unit="LBS">0</weight>
            <location unit="IN">
                <x> 82.44 </x>
                <y> -58.03 </y>
                <z> -65.75 </z>
            </location>
        </pointmass>
        <pointmass name="Right_Gear_Testing">
            <weight unit="LBS">0</weight>
            <location unit="IN">
                <x> 82.44 </x>
                <y> 58.03 </y>
                <z> -65.75 </z>
            </location>
        </pointmass>
    </mass_balance>


    <ground_reactions>
        <contact type="BOGEY" name="NOSE_LG">  <!--0-->
            <location unit="IN">
                <x> -139.76 </x>
                <y> 0 </y>
                <z> -81.2 </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"> 14000</spring_coeff>
            <damping_coeff unit="LBS/FT/SEC">3500</damping_coeff>
            <max_steer unit="DEG"> 60</max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="LEFT_MLG"> <!--1-->
            <location unit="IN">
                <x> 82.44 </x>
                <y> -58.03 </y>
                <z> -65.75 </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"> 55000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 11000</damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> LEFT </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="RIGHT_MLG"> <!--2-->
            <location unit="IN">
                <x> 82.44 </x>
                <y> 58.03 </y>
                <z> -65.75 </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"> 55000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 11000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable>1</retractable>
        </contact>

       <!-- ========================================================================-->


        <contact type="STRUCTURE" name="W_LEFT_FOLD"> <!--3-->
            <location unit="IN">
                <x> 171 </x>
                <y> -213 </y>
                <z> 7.5 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 10 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 200 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="STRUCTURE" name="W_RIGHT_FOLD"><!-- 4-->
            <location unit="IN">
                <x> 171 </x>
                <y> 213 </y>
                <z> 7.5 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 10 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 200 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="STRUCTURE" name="W_LEFT"> <!--5-->
            <location unit="IN">
                <x> 113</x>
                <y> -135.3 </y>
                <z> 15.76 </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"> 200 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="STRUCTURE" name="W_RIGHT"> <!--6-->
            <location unit="IN">
                <x> 113 </x>
                <y> 135.3 </y>
                <z> 15.76</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"> 200 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="STRUCTURE" name="VT"> <!--7-->
            <location unit="IN">
                <x> 312 </x>
                <y> 0 </y>
                <z> 14.5 </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"> 200 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="STRUCTURE" name="RADOME"> <!--8-->
            <location unit="IN">
                <x> -172 </x>
                <y> 0 </y>
                <z> 39.5 </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"> 100 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="BELLY"> <!--9-->
            <location unit="IN">
                <x> -173 </x>
                <y> 0 </y>
                <z> -39.3 </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"> 100000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 3000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="STRUCTURE" name="NOSE"> <!--10-->
            <location unit="IN">
                <x> -317 </x>
                <y> 0 </y>
                <z> -10 </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"> 100000 </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>1</retractable>
        </contact>
        <contact type="STRUCTURE" name="NOZZLE"> <!--11-->
            <location unit="IN">
                <x> 315 </x>
                <y> 0 </y>
                <z> -26 </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"> 100000 </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>1</retractable>
        </contact>
        <contact type="STRUCTURE" name="TOP"> <!--12-->
            <location unit="IN">
                <x> 0 </x>
                <y> 0 </y>
                <z> 60</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"> 100000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="STRUCTURE" name="FICTIVE_REAR"> <!--13-->
            <location unit="IN">
                <x>120 </x>
                <y>0</y>
                <z> -20 </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"> 100000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="FICTIVE_FRONT"> <!--14-->
            <location unit="IN">
                <x>-334.6</x>
                <y>0</y>
                <z> -100 </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"> 10 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>


<!--=========================================================-->
        <!--DON'T  MODIFY:  Used to animate LG  at rest    with  extended  position-->
        <!--we are missing an extension dimension definition within LG-->

        <contact type="STRUCTURE" name="NOSE_LG_under">  <!--CP 15-->
            <location unit="IN">
                <x> -139.76 </x>
                <y> 0 </y>
                <z> -92 </z>
            </location>
            <static_friction> 0.001 </static_friction>
            <dynamic_friction> 0.001 </dynamic_friction>
            <rolling_friction> 0.0001 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10</spring_coeff>
            <damping_coeff unit="LBS/FT/SEC">2</damping_coeff>
            <max_steer unit="DEG"> 0.0</max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="STRUCTURE" name="LEFT_MLG_under"> <!--CP 16-->
            <location unit="IN">
                <x> 82.44 </x>
                <y> -58.03 </y>
                <z> -78 </z>
            </location>
            <static_friction> 0.001 </static_friction>
            <dynamic_friction> 0.001 </dynamic_friction>
            <rolling_friction> 0.0001 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10</spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2</damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE</brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="STRUCTURE" name="RIGHT_MLG_under"> <!--CP 17-->
            <location unit="IN">
                <x> 82.44 </x>
                <y> 58.03 </y>
                <z> -78 </z>
            </location>
            <static_friction> 0.001 </static_friction>
            <dynamic_friction> 0.001 </dynamic_friction>
            <rolling_friction> 0.0001 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable>1</retractable>
        </contact>


    </ground_reactions>
    <propulsion>
        <engine file="PW-J57P-new">
            <location unit="IN">
                <x> 317 </x>
                <y> 0 </y>
                <z> 0 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>0</feed>
            <thruster file="direct-new">
                <location unit="IN">
                    <x> 317 </x>
                    <y> 0 </y>
                    <z> 0 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>

        <tank type="FUEL">
            <location unit="IN">
                <x> 0 </x>
                <y> 0 </y>
                <z> -16.3492 </z>
            </location>
            <priority>1</priority>
            <capacity unit="LBS"> 5 </capacity>
            <contents unit="LBS"> 0 </contents>
        </tank>

    </propulsion>
    <!--<system file="aero"/>-->
    <system file="fcs"/>
    <system file="steady-behaviour"/>
    
    <!-- _________________-->
    <system file="electrical-fdm-custom"/>
    <system file="electrical-fdm"/>
    <system file="electrical-lights"/>
   <!-- _____Carrier____________-->

   <system file="catapult_free"/>
   <system file="holdback_free"/>
    <!-- _________________-->

    <system file="init-carrier"/>
    
     <system file="cat-hold"/>
    
    <system file="hook"/>
    
    <!-- _____FCS______________-->
    <system file="speedbrake"/>
    <system file="wings"/>
    <!--<system file="FCS-Stall_Spin"/>-->
    <system file="BLC"/>
    <system file="propulsion"/>
    <!-- _________________-->
    <system file="crash-detect"/>
    <system file="crash-sink-anim"/>
    <!-- _________________-->
    
    <system file="fuel"/>
    <system file="probe-refuel"/>
    <system file="refuel"/>
    <!-- _________________-->

    <!-- _________________-->
    <system file="brake"/>
    <system file="landing-gear"/>
    <!-- _________________-->
    <system file="instruments"/>
    <system file="annunciator"/>
    <system file="aoa-new"/>
    <!-- _________________-->
    <system file="canopy"/>
    <!-- _________________-->
    
    <system file="mule-crus"/>
    <!-- _________________-->
    <system file="blackout"/>
    <system file="cpdrag"/>
    
    



    <flight_control name="FCS: F-8E">


    </flight_control>

    <aerodynamics>
        <!--Variable incidence wings,   the max incidence 7 deg  0.12217305 rad    -->
        <!--french version Variable incidence wings,   the max incidence 8 deg  0.13962634 rad     defined within  systems/wings ( line 124)-->
        <!--<function name="aero/alpha-rad-w-incidence">
            <description>Addition of incidence due to UP</description>
                <sum>
                    <property>aero/alpha-rad</property>
                    <property>fcs/wings-pos-rad</property>
                </sum>
        </function>-->
        <!--Voir wings.xml-->



       <!-- Here from A-7E by Dave-->
        <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
                    </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>

        <!--CL-alpha:      3.5 per radian
                           CL-0:          0.08
                           CL-max:        1
                           CD-0:          0.021    must be checked with data tunnel
			K:             0.09-->

        <!--document 19930085859_1993085859.pdf with SviTEPT RACK 35O, ASPECT RATIO 4, TAPER RATIO 0.8,
        AND NACA 65A006 AIRFOIL SECTION.-->
        <!--Zero-lift drag coefficient: 0.0133-->
        <!--CL-alpha:      3.5 per radian
            CL-0:          0.08
            CL-max:        1
            CD-0:          0.021  must be checked with data tunnel
            K:             0.09
            NACA 65A006  -->
        <!--lift curve calculated with wing pos-norm  0  ==> 0 degree TEFlap 0 LEFlap 0-->
        <!--lift curve calculated with wing pos-norm  1  ==> 8 degree TEFlap 32 LEFlap 12-->


            <function name="aero/function/krootCLalpha">
                <description>kLift_due_to_alpha</description>
                <product>
                    <sum>
                        <property>systems/wing-lift_coeff_add</property>
                        <value>1</value>
                    </sum>
                    <table>
                        <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <independentVar lookup="column">fcs/wings-pos-norm</independentVar>
                          <tableData name="lw">

                                                        00.000000		01.000000
                            -15.00000		-00.72130		-00.22030
                            -14.50000		-00.70880		-00.21470
                            -14.00000		-00.69700		-00.20910
                            -13.50000		-00.68590		-00.20350
                            -13.00000		-00.67550		-00.19820
                            -12.50000		-00.66670		-00.19320
                            -12.00000		-00.65890		-00.18860
                            -11.50000		-00.65140		-00.18490
                            -11.00000		-00.64570		-00.18270
                            -10.50000		-00.63930		-00.18410
                            -10.00000		-00.63390		-00.19700
                            -09.50000		-00.63030		-00.19610
                            -09.00000		-00.62800		-00.18170
                            -08.50000		-00.62770		-00.15770
                            -08.00000		-00.63370		-00.12070
                            -07.50000		-00.63870		-00.06510
                            -07.00000		-00.63000		00.02080
                            -06.50000		-00.61290		00.54750
                            -06.00000		-00.58950		00.60180
                            -05.50000		-00.56140		00.64070
                            -05.00000		-00.52190		00.69190
                            -04.50000		-00.47850		00.73390
                            -04.00000		-00.42600		00.78200
                            -03.50000		-00.37310		00.82850
                            -03.00000		-00.32020		00.87710
                            -02.50000		-00.26730		00.92320
                            -02.00000		-00.21400		00.96910
                            -01.50000		-00.16050		01.00840
                            -01.00000		-00.10700		01.08538
                            -00.50000		-00.05350		01.16236
                            00.00000		00.00000		01.23933
                            00.50000		00.05350		01.31631
                            01.00000		00.10700		01.39329
                            01.50000		00.16050		01.47027
                            02.00000		00.21400		01.47027
                            02.50000		00.26730		01.47934
                            03.00000		00.32020		01.47854
                            03.50000		00.37310		01.47682
                            04.00000		00.42600		01.47528
                            04.50000		00.47850		01.47595
                            05.00000		00.51800		01.47630
                            05.50000		00.56380		01.47660
                            06.00000		00.58950		01.47610
                            06.50000		00.61300		01.43530
                            07.00000		00.63020		01.39330
                            07.50000		00.63910		01.35630
                            08.00000		00.63440		01.32860
                            08.50000		00.62890		01.31990
                            09.00000		00.62960		01.31810
                            09.50000		00.63220		01.31790
                            10.00000		00.63600		01.31940
                            10.50000		00.64160		01.32230
                            11.00000		00.64820		01.32590
                            11.50000		00.65420		01.33010
                            12.00000		00.66180		01.33440
                            12.50000		00.66960		01.33850
                            13.00000		00.67860		01.34180
                            13.50000		00.68910		01.34320
                            14.00000		00.70030		01.33720
                            18.00000           00.65000               01.30000
                            20.00000           00.62000               01.12200
                            25.00000           00.61000               01.00000
                            40.00000           00.60000               00.90000
                            </tableData>
                        </table>
                    </product>
            </function>

            
<!--RE 3000000-->
            <function name="aero/function/ktipCLalpha">
                <description>kwing tip_Lift_due_to_alpha</description>
                <product>
                    <sum>
                        <property>systems/wing-lift_coeff_add</property>
                        <value>1</value>
                    </sum>
                    <table>
                        <independentVar>aero/alpha-wing-deg</independentVar>
                        <tableData>
                            -14         -1.036299
                            -13         -1.076908
                            -12         -1.206191
                            -11         -1.154813
                            -10         -1.089431
                            -9         -1.020265
                            -8        -0.9251668
                            -7        -0.7986193
                            -6        -0.6783747
                            -5        -0.5491416
                            -4        -0.4273973
                            -3        -0.2967012
                            -2        -0.1948231
                            -1       -0.09816584
                            0      1.728283e-10
                            1        0.09816586
                            2         0.1948231
                            3         0.2967018
                            4         0.4274075
                            5         0.5491644
                            6         0.6784037
                            7         0.7986763
                            8         0.9252383
                            9          1.020225
                            10          1.089411
                            11          1.154854
                            12          1.206384
                            13          1.075839
                            14          1.037182
                            15          1.002985
                            16         0.8640548
                            17         0.7118886
                            18         0.7352895
                            19         0.7630147
                            20         0.7861199
                            21         0.8082324
                            22         0.8289926
                            40          0.600000
                        </tableData>
                    </table>
                </product>
            </function>

<!--RE 3000000-->
            <function name="aero/function/ktipLeCLalpha">
                <description>kwing tip_Lift_with_LE_due_to_alpha</description>
                <product>
                    <sum>
                        <property>systems/wing-lift_coeff_add</property>
                        <value>1</value>
                    </sum>
                    <table>
                        <independentVar>aero/alpha-wing-deg</independentVar>

                        <tableData>

                            -10.00		-00.3824
                            -09.50		-00.3652
                            -09.00		-00.3510
                            -08.50		-00.3383
                            -08.00		-00.3270
                            -07.50		-00.3168
                            -07.00		-00.3077
                            -06.50		-00.3006
                            -06.00		-00.2959
                            -05.00		-00.5617
                            -04.50		-00.5227
                            -04.00		-00.4756
                            -03.50		-00.4263
                            -03.00		-00.3749
                            -02.50		-00.3222
                            -02.00		-00.2688
                            -01.50		-00.2161
                            -01.00		-00.1632
                            -00.50		-00.1098
                            00.00		-00.0561
                            00.50		-00.0020
                            01.00		00.0514
                            01.50		00.1055
                            02.00		00.1589
                            02.50		00.2125
                            03.00		00.2662
                            03.50		00.3197
                            04.00		00.3731
                            04.50		00.4266
                            05.00		00.4802
                            05.50		00.5336
                            06.00		00.5866
                            06.50		00.6397
                            07.00		00.6969
                            07.50		00.7557
                            08.00		00.8120
                            08.50		00.8674
                            09.00		00.9248
                            09.50		00.9786
                            10.00		01.0125
                            10.50		01.0622
                            11.00		01.1118
                            11.50		01.1604
                            12.00		01.2085
                            12.50		01.2551
                            13.00		01.2977
                            13.50		01.3406
                            14.50		01.4541
                            15.00		01.4801
                            15.50		01.4923
                            16.00		01.4907
                            16.50		01.4843
                            17.00		01.4685
                            17.50		01.4449
                            18.00		01.4084
                            18.50		01.3750
                            19.00		01.3418
                            19.50		01.3171
                            20.00		01.3046
                            20.500      1.2871
                            21.000      1.2780
                            21.500      1.2577
                            22.000      1.2528
                            22.500      1.2474
                            23.000      1.2305
                            23.500      1.2253
                            24.000      1.2132
                            25.000      1.1513
                            26.000      1.0598
                            40              0.700000
                        </tableData>
                    </table>
                </product>
            </function>





            <axis name="LIFT">

                <function name="aero/coefficient/CLralpha">
                    <description>wing_root_Lift_due_to_alpha</description>
                    <product>
                        <property>systems/crash-detect/aero-sw</property>
                        <property>aero/qbar-psf</property>
                        <property>metrics/Sw-sqft</property>
                        <property>aero/function/kCLge</property>
                        <property>aero/function/krootCLalpha</property>
                        <value>0.80</value>
                    </product>
                </function>

                <function name="aero/coefficient/CLtalpha">
                    <description>wing_tip_Lift_due_to_alpha</description>
                    <product>
                        <property>systems/crash-detect/aero-sw</property>
                        <property>aero/qbar-psf</property>
                        <property>metrics/Sw-sqft</property>
                        <property>aero/function/kCLge</property>
                        <property>aero/function/ktipCLalpha</property>
                        <property>systems/wings-fold/right-wing</property>
                        <property>systems/wings-fold/left-wing</property>
                        <property>fcs/wing-incidence-down</property>
                        <value>0.20</value>
                    </product>
                </function>


                <function name="aero/coefficient/CLtlealpha">
                    <description>wing_tip_Lift_due_to_alpha</description>
                    <product>
                        <property>systems/crash-detect/aero-sw</property>
                        <property>aero/qbar-psf</property>
                        <property>metrics/Sw-sqft</property>
                        <property>aero/function/kCLge</property>
                        <property>aero/function/ktipLeCLalpha</property>
                        <property>systems/wings-fold/right-wing</property>
                        <property>systems/wings-fold/left-wing</property>
                        <property>fcs/wing-incidence-up</property>
                        <value>0.20</value>
                    </product>
                </function>

            <!--only UP or DOWN  of  Flaps  synchro with Wing incidence  Flap => 32 degres + wing => 8 deg  = 40-->
            <!--===we want lft coef=1   at wing 8 deg ======= we have it ==>> 0.5 wings + 0.5 flap -->

            <function name="aero/coefficient/dCLBLC">
            <description>Delta_Lift_due_to_BLC</description>
            <product>
                <property>systems/crash-detect/aero-sw</property>
                <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>systems/BLC/active</property>
                    <!--<property>fcs/wings-pos-norm</property>-->
                    <value> 0.20 </value>
            </product>
            </function>

            <function name="aero/coefficient/dCLDlef">
                <!--only with wing incidence to Zero-->
                <description>Delta_Lift_due_to_leading_edge_flap_deflection</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <table>
                        <independentVar lookup="row">fcs/leflap-pos-rad</independentVar>
                        <independentVar lookup="column">fcs/wings-pos-norm</independentVar>
                        <tableData>
                                                        0               1
                            0.0000	0.0000       0000
                            0.2100	0.0160       0000

                        </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/coefficient/dCLsb">
                <description>Delta_Lift_due_to_speedbrake</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/speedbrake-pos-deg</property>
                    <value>0.0008</value>
                </product>
            </function>

           <!-- with efficiency due to wing incidence a guess must be fixed-->
            <function name="aero/coefficient/CLde">
                <description>Lift_due_to_Elevator_Deflection</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <sum>
                        <property>fcs/elevator-pos-rad</property>
                        <product>
                            <property>fcs/wings-pos-norm</property>
                            <value>-0.04</value><!---0.04-->
                        </product>
                    </sum>
                    <value>0.18</value>
                </product>
            </function>

            <!--<function name="aero/coefficient/buffet">
                <description>Buffet at high alpha</description>
                <product>
                    <property>systems/alpha_buffet/sine_wave</property>
                    <property>systems/alpha_buffet/strength</property>
                </product>
            </function>-->

        </axis>

        <axis name="DRAG">
            <!--Doc NACA L51A02 page 25 and doc NACA RM N9A21 page 17
                    Mach 1.8 extrapolated-->
            <function name="aero/coefficient/CDclrmach">
                <description>wing_root_Drag_due_to_CL_due_to_Mach</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCDge</property>
                    <property>systems/wing-drag_coeff</property> <!--value=1-->
                    <value>0.80</value>
                    <table name="drm">
                        <independentVar lookup="row">aero/function/krootCLalpha</independentVar>
                        <independentVar lookup="column">velocities/mach</independentVar>
                        <tableData>

                                                        00.600000		00.875000		00.930000		01.200000           01.800000
                           -00.200000		00.010000		00.010000		00.030000		00.033000           00.026800
                           00.000000		00.006000		00.007000		00.020000		00.026000           00.023000
                           00.100000		00.006500		00.007000		00.021000		00.028000           00.026800
                           00.200000		00.010000		00.010000		00.027000		00.038000           00.030660
                           00.300000		00.020000		00.020000		00.040000		00.053000           00.042160
                           00.400000		00.030000		00.030000		00.050000		00.070000           00.053600
                           00.500000		00.050000		00.050000		00.070000		00.090000           00.069000
                           00.600000		00.090000		00.070000		00.090000		00.120000           00.092000
                           00.700000		00.150000		00.100000		00.120000		00.150000           00.115000
                           00.800000		00.220000		00.220000		00.160000		00.180000           00.138000
                        </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/coefficient/CDcltmach">
                <description>wing_tip_Drag_due_to_CL_due_to_Mach</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCDge</property>
                    <property>systems/wing-drag_coeff</property> <!--value=1-->
                    <value>0.20</value>
                    <table name="dtm">
                        <independentVar lookup="row">aero/function/ktipCLalpha</independentVar>
                        <independentVar lookup="column">velocities/mach</independentVar>
                        <tableData>

                            00.600000		00.875000		00.930000		01.200000           01.800000
                            -00.200000		00.010000		00.010000		00.030000		00.033000           00.026800
                            00.000000		00.006000		00.007000		00.020000		00.026000           00.023000
                            00.100000		00.006500		00.007000		00.021000		00.028000           00.026800
                            00.200000		00.010000		00.010000		00.027000		00.038000           00.030660
                            00.300000		00.020000		00.020000		00.040000		00.053000           00.042160
                            00.400000		00.030000		00.030000		00.050000		00.070000           00.053600
                            00.500000		00.050000		00.050000		00.070000		00.090000           00.069000
                            00.600000		00.090000		00.070000		00.090000		00.120000           00.092000
                            00.700000		00.150000		00.100000		00.120000		00.150000           00.115000
                            00.800000		00.220000		00.220000		00.160000		00.180000           00.138000
                        </tableData>
                    </table>
                </product>
            </function>


            <function name="aero/coefficient/CDDlef">
                <!--only with wing incidence to Zero-->
                <description>Drag_due_to_leading_edge_flap_deflection</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/leflap-pos-norm</property>
                    <table>
                        <independentVar>fcs/wings-pos-norm</independentVar>
                        <tableData>
                            0   0.0025
                            1   0.000
                        </tableData>
                    </table>
                    <value>0.0025</value>
                </product>
            </function>

            <function name="aero/coefficient/CDwing">
                <description>Drag_due-to_wing_up</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/wings-pos-norm</property>
                    <value>0.00500</value>
                </product>
            </function>

            <function name="aero/coefficient/CDgear">
                <description>Drag_due_to_gear</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>gear/unit[0]/pos-norm</property>
                    <property>gear/unit[1]/pos-norm</property>
                    <property>gear/unit[2]/pos-norm</property>
                    <value>0.0200</value>
                </product>
            </function>
            <function name="aero/coefficient/CDsb">
                <description>Drag_due_to_speedbrakes</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/speedbrake-pos-deg</property>
                    <value>0.0010</value>
                </product>
            </function>
            <function name="aero/coefficient/CDbeta">
                <description>Drag_due_to_sideslip</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <table>
                        <independentVar>aero/beta-rad</independentVar>
                        <tableData>
                            -1.5700	1.2000
                            -0.2600	0.0300
                            0.0000	0.0000
                            0.2600	0.0300
                            1.5700	1.2000
                        </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/coefficient/CDde">
                <description>Drag_due_to_Elevator_Deflection</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <table>
                        <independentVar lookup="row">fcs/elevator-pos-rad</independentVar>
                        <independentVar lookup="column">fcs/wings-pos-norm</independentVar>
                        <tableData>
                                            0           1
                            -0.35   0.02    0.0248
                                0       0           0
                            0.35    0.02    0.0152
                        </tableData>
                    </table>
                </product>
            </function>

            <!--not realistic , only for animation with crash in water -->
            <function name="aero/coefficient/CDgear_water">
                <description>Drag_due_to_crashing_with_gear_in_water</description>
                <product>
                    <property>fcs/drag-gear-in-water-switch</property>
                    <table>
                        <independentVar>velocities/vc-kts</independentVar>
                        <tableData>
                            0     0
                            30    900
                            50    2700
                            90    10000
                            110  100000
                            220  10000000
                        </tableData>
                    </table>
                </product>
            </function>
        </axis>



        <axis name="ROLL">
            <function name="aero/coefficient/Clb">
                <description>Roll_moment_due_to_beta</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/beta-rad</property>
                    <value>-0.0500</value>
                </product>
            </function>

            <!--Stall >>Spinning  temporary removed-->
            <!--<function name="aero/coefficient/Clalpha">
                <description>Roll_moment_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/w_asym-coefficient</property>
                    <value>0.3</value>
                </product>
            </function>-->

            <!--Roll damping-->
            <function name="aero/coefficient/Clp">
                <description>Roll_moment_due_to_roll_rate</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <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>
                    <table>
                        <independentVar>fcs/wings-pos-norm</independentVar>
                        <tableData>
                            0   -0.6
                            1   -0.7
                        </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/coefficient/Clr">
                <description>Roll_moment_due_to_yaw_rate</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <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>fcs/wings-pos-norm</independentVar>
                        <tableData>
                            0   0.07
                            1   0.05
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/Clda">
                <description>Roll_moment_due_to_aileron</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                    <table>
                        <independentVar lookup="row">velocities/mach</independentVar>
                        <independentVar lookup="column">fcs/wings-pos-norm</independentVar>

                        <tableData>
                                                  0                 1
                            0.0000	0.1100   0.1800
                            2.0000	0.0370    0.0370
                        </tableData>
                    </table>
                      <!--Stall >>Spinning, Lost of efficiency-->
                      <!--base FCS-Stall_Spin revoir le principe, raisonnement "marche d'escalier"-->
                    <!--<table>
                        <independentVar>fcs/w_asym-coefficient</independentVar>
                        <tableData>
                            0.0             1.0
                            0.002         0.7
                            0.010         0.2
                        </tableData>
                </table>-->

                </product>
            </function>
            <function name="aero/coefficient/Cldr">
                <description>Roll_moment_due_to_rudder</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <table>
                        <independentVar>fcs/wings-pos-norm</independentVar>
                        <tableData>
                            0   0.01
                            1   0.01
                        </tableData>
                    </table>
                </product>
            </function>
        </axis>

        <axis name="PITCH">
            <function name="aero/coefficient/Cmralpha">
                <description>wing_root_Pitch_moment_due_to_alpha</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <value>0.80</value>
                    <table name="prm">
                       <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <independentVar lookup="column">fcs/wings-pos-norm</independentVar>
                          <tableData>
                                                            0.0000                   1.0000
                        -15.00000		00.05190		00.03285
                        -14.50000		00.04880		00.02995
                        -14.00000		00.04580		00.02718
                        -13.50000		00.04280		00.02440
                        -13.00000		00.03980		00.02165
                        -12.50000		00.03680		00.01890
                        -12.00000		00.03370		00.01610
                        -11.50000		00.03080		00.01355
                        -11.00000		00.02790		00.01108
                        -10.50000		00.02460		00.00840
                        -10.00000		00.02110		00.00615
                        -09.50000		00.01750		00.00298
                        -09.00000		00.01330		-00.00160
                        -08.50000		00.00820		-00.00765
                        -08.00000		-00.00180		-00.01933
                        -07.50000		-00.00850		-00.02880
                        -07.00000		-00.01140		-00.03623
                        -06.50000		-00.01170		-00.06893
                        -06.00000		-00.00990		-00.06720
                        -05.50000		-00.00640		-00.06324
                        -05.00000		-00.00350		-00.06028
                        -04.50000		00.00060		-00.05585
                        -04.00000		00.00070		-00.05555
                        -03.50000		00.00070		-00.05523
                        -03.00000		00.00070		-00.05493
                        -02.50000		00.00070		-00.05460
                        -02.00000		00.00060		-00.05438
                        -01.50000		00.00040		-00.05423
                        -01.00000		00.00030		-00.05400
                        -00.50000		00.00010		-00.05388
                        00.00000		00.00000		-00.05369
                        00.50000		-00.00010		-00.05343
                        01.00000		-00.00030		-00.05338
                        01.50000		-00.00040		-00.05308
                        02.00000		-00.00060		-00.05196
                        02.50000		-00.00070		-00.05075
                        03.00000		-00.00070		-00.04944
                        03.50000		-00.00070		-00.04813
                        04.00000		-00.00070		-00.04682
                        04.50000		-00.00060		-00.04541
                        05.00000		00.00210		-00.04140
                        05.50000		00.00370		-00.03763
                        06.00000		00.00990		-00.02988
                        06.50000		00.01170		-00.02730
                        07.00000		00.01140		-00.02778
                        07.50000		00.00840		-00.03255
                        08.00000		00.00150		-00.04298
                        08.50000		-00.00850		-00.05605
                        09.00000		-00.01360		-00.06313
                        09.50000		-00.01790		-00.06910
                        10.00000		-00.02150		-00.07420
                        10.50000		-00.02510		-00.07918
                        11.00000		-00.02840		-00.08375
                        11.50000		-00.03130		-00.08788
                        12.00000		-00.03430		-00.09205
                        12.50000		-00.03740		-00.09628
                        13.00000		-00.04040		-00.10035
                        13.50000		-00.04340		-00.10438
                        14.00000		-00.04660		-00.10950
                        14.50000		-00.05020		-00.11430
                        15.00000		-00.05440		-00.12008
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/Cmtalpha">
                <description>wing_tip_Pitch_moment_due_to_alpha</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <value>0.20</value>
                    <table name="ptm">
                        <independentVar>aero/alpha-wing-deg</independentVar>
                          <tableData>
                            -14       -0.01885384
                            -13       -0.03842179
                            -12       -0.02174873
                            -11       -0.01266822
                            -10      -0.004588366
                            -9       0.003576898
                            -8       0.006921423
                            -7       0.003330527
                            -6       0.001301623
                            -5      -0.002568254
                            -4       -0.00460672
                            -3      -0.008935088
                            -2      -0.006526491
                            -1      -0.003054819
                            0      2.357382e-10
                            1       0.003054819
                            2       0.006526512
                            3       0.008934981
                            4         0.0046044
                            5       0.002562999
                            6      -0.001308367
                            7      -0.003343697
                            8      -0.006937832
                            9      -0.003568542
                            10       0.004593342
                            11        0.01266149
                            12        0.02171153
                            13        0.03796354
                            14        0.01796081
                            15       0.005273767
                            16       -0.01673217
                            17       -0.04267304
                            18       -0.04918116
                            19       -0.05542727
                            20        -0.0618301
                            21       -0.06806703
                            22       -0.07413074
                        </tableData>
                    </table>
                </product>
            </function>



            <function name="aero/coefficient/Cmfalpha">
                <description>fuse_Pitch_moment_due_to_alpha</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/alpha-rad</property>
                    <value>-0.008</value>
                </product>
             </function>

            <function name="aero/coefficient/Cmde">
                <description>Pitch_moment_due_to_elevator</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
		    <property>fcs/elevator-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-0.950
                              2.0000	-0.250
                          </tableData>
                      </table>
                </product>
            </function>

            <function name="aero/coefficient/Cmgear">
                <description>Pitch_due_to_gear</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>gear/unit[0]/pos-norm</property>
                    <property>gear/unit[1]/pos-norm</property>
                    <property>gear/unit[2]/pos-norm</property>
                    <value>-0.0600</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmq">
                <description>Pitch_moment_due_to_pitch_rate</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <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>
                    <table>                       
			<independentVar lookup="row">fcs/wings-pos-norm</independentVar>
			<independentVar lookup="column">velocities/mach</independentVar>
			<tableData>
				    0.00	2.00
			    0   -45.0      -75.0
			    1   -32.0      -32.0
			</tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/Cmadot">
                <description>Pitch_moment_due_to_alpha_rate</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <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>
                    <table>
                        <independentVar>fcs/wings-pos-norm</independentVar>
                        <tableData>
                            0   -10.8
                            1   -12.7
                        </tableData>
                    </table>
                </product>
            </function>

           <!-- <function name="aero/coefficient/Cmthr">
                <description>Pitch_moment_due_to_thrust</description>
                <product>
                    <property>propulsion/engine/thrust-lbs</property>
                    <table>
                        <independentVar>fcs/wings-pos-norm</independentVar>
                        <tableData>
                            0   0.000
                            1   0.01
                        </tableData>
                    </table>
                </product>
            </function>-->
        </axis>

        <axis name="YAW">
            <function name="aero/coefficient/Cnb">
                <description>Yaw_moment_due_to_beta</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/beta-rad</property>
                    <value>0.12</value>
                </product>
            </function>

            <!--Stall >>Spinning-->
           <!-- <function name="aero/coefficient/Cnalpha">
                <description>Yaw_moment_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/w_asym-coefficient</property>
                </product>
            </function>-->

            <function name="aero/coefficient/Cnr">
                <description>Yaw_moment_due_to_yaw_rate</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <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>fcs/wings-pos-norm</independentVar>
                        <tableData>
                            0   -15.000
                            1   -20.000
                        </tableData>
                    </table>
                </product>
            </function>

            <!--FIXME getting trouble with it-->
            <function name="aero/coefficient/Cnp">
                <description>Yaw_moment_due_to_roll_rate</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <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>-0.030</value>-->
                    <value>-0.00</value>
                </product>
            </function>
            <function name="aero/coefficient/Cndr">
                <description>Yaw_moment_due_to_rudder</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>-0.1200</value>
                </product>
            </function>
            <function name="aero/coefficient/Cnda">
                <description>Adverse_yaw</description>
                <product>
                    <property>systems/crash-detect/aero-sw</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                    <value>0.0000</value>
                </product>
            </function>
        </axis>

    </aerodynamics>


     <external_reactions>

        <force name="catapult" frame="LOCAL">
            <location unit="IN">
                <x>  -30 </x>
                <y>    0.0 </y>
                <z>  -39.0 </z>
            </location>
            <direction>
                <x>1</x>
                <y>0</y>
                <z>0.08</z>
            </direction>
        </force>

       
        
        <!--Catapult   vertical force when necessary to keep the right position on the catapult rail-->
        <force name="cat-hold" frame="BODY">
        <location unit="IN">
            <x>  -30 </x>
            <y>    0.0 </y>
            <z>  -39.0 </z>
        </location>
        <direction>
            <x>0</x>
            <y>0</y>
            <z>1 </z>
        </direction>
        </force>

        <force name="holdback" frame="BODY">
        <location unit="IN">
            <x> 211</x>
            <y>    0.0 </y>
            <z>  -39.0 </z>
        </location>
        <direction>
            <x>   -1.0 </x>
            <y>    0.0 </y>
            <z>    -0.15 </z>
        </direction>
        </force>

        
        <force name="hook" frame="BODY">
        <location unit="IN">
            <x> 100 </x>
            <y> 0.0 </y>
            <z>  -15.0 </z>
        </location>
        <direction>
            <x>  -1  </x>
            <y>0</y>
            <z>   0.1</z>
        </direction>
        </force>

        <force name="mule" frame="BODY">
        <location unit="IN">
            <x>  -139 </x>
            <y>    0.0 </y>
            <z>  -71.0 </z>
        </location>
        <direction>
            <x>1</x>
            <y>0</y>
            <z>0</z>
        </direction>
        </force>

        <force name="taxi" frame="BODY">
            <location unit="IN">
                <x>  -139 </x>
                <y>    0.0 </y>
                <z>  -71.0 </z>
            </location>
            <direction>
                <x>1</x>
                <y>0</y>
                <z>0.3</z>
            </direction>
        </force>

        <force name="cp1-bellydragx" frame="BODY">
            <location unit="IN">
                <x>  0 </x>
                <y>  0.0 </y>
                <z>  -5 </z>
            </location>
            <direction>
                <x>-1</x>
                <y>0</y>
                <z>0.1</z>
            </direction>
        </force>

        <force name="nose-gear" frame="BODY">
            <location unit="IN">
                <x> -139.76 </x>
                <y> 0 </y>
                <z> -81.6 </z>
            </location>
            <direction>
                <x>1</x>
                <y>0</y>
                <z>0</z>
            </direction>
        </force>
        <force name="left-gear" frame="BODY">
	    <location unit="IN">
                <x> 82.44 </x>
                <y> -58.03 </y>
                <z> -65.75 </z>
	    </location>
            <direction>
                <x>1</x>
                <y>0</y>
                <z>0</z>
            </direction>
        </force>
        <force name="right-gear" frame="BODY">
            <location unit="IN">
                <x> 82.44 </x>
                <y> 58.03 </y>
                <z> -65.75 </z>
            </location>
            <direction>
                <x>1</x>
                <y>0</y>
                <z>0</z>
            </direction>
        </force>
        <force name="nose-gear-bump" frame="BODY">
            <location unit="IN">
                <x> -139.76 </x>
                <y> 0 </y>
                <z> -81.6 </z>
            </location>
            <direction>
                <x>0</x>
                <y>0</y>
                <z>-1</z>
            </direction>
        </force>
        <force name="left-gear-bump" frame="BODY">
            <location unit="IN">
                <x> 82.44 </x>
                <y> -58.03 </y>
                <z> -65.75 </z>
            </location>
            <direction>
                <x>0</x>
                <y>0</y>
                <z>1</z>
            </direction>
        </force>
        <force name="right-gear-bump" frame="BODY">
            <location unit="IN">
                <x> 82.44 </x>
                <y> 58.03 </y>
                <z> -65.75 </z>
            </location>
            <direction>
                <x>0</x>
                <y>0</y>
                <z>1</z>
            </direction>
        </force>

        <force name="fusedragx" frame="BODY">
            <location unit="IN">
                <x>  0 </x>
                <y>  0.0 </y>
                <z>  0 </z>
            </location>
            <direction>
                <x>-1</x>
                <y>0</y>
                <z>0.1</z>
            </direction>
        </force>

        <force name="catapult_free" frame="BODY">
            <location unit="IN">
                <x> -30.0 </x>
                <y>  0.0 </y>
                <z>  0 </z>
            </location>
            <direction>
                <x> 1</x>
                <y>  0 </y>
                <z> 0.35 </z>
            </direction>
        </force>

        <force name="holdback_free" frame="BODY">
            <location unit="IN">
                <x> 40 </x>
                <y>  0.0 </y>
                <z>  -20.0 </z>
            </location>
            <direction>
                <x>   -1.0 </x>
                <y>    0.0 </y>
                <z>    0.0 </z>
            </direction>
        </force>


        <force name="crash-force" frame="LOCAL">
            <location unit="IN">
                <x> 0 </x>
                <y>  0 </y>
                <z> 0 </z>
            </location>
            <direction>
                <x>   0 </x>
                <y>    0.0 </y>
                <z>    1.0 </z>
            </direction>
        </force>

        <force name="crash-force-y" frame="BODY">
            <location unit="IN">
                <x> 0 </x>
                <y>  10 </y>
                <z> 0 </z>
            </location>
            <direction>
                <x>   0 </x>
                <y>    0.0 </y>
                <z>    1.0 </z>
            </direction>
        </force>

        <force name="crash-force-x" frame="BODY">
            <location unit="IN">
                <x> 100 </x>
                <y>  0 </y>
                <z> 0 </z>
            </location>
            <direction>
                <x>   0 </x>
                <y>    0.0 </y>
                <z>    1.0 </z>
            </direction>
        </force>

        <!--ONLY FOR TESTING-->
        <force name="testing1" frame="BODY">
            <location unit="IN">
                <x>200</x>
                <y>  0 </y>
                <z> 0 </z>
            </location>
            <direction>
                <x>   0 </x>
                <y>    0.0 </y>
                <z>    -1.0 </z>
            </direction>
        </force>
        <!--ONLY FOR TESTING-->
        <force name="testing2" frame="BODY">
            <location unit="IN">
                <x>-36</x>
                <y>  0 </y>
                <z> 0 </z>
            </location>
            <direction>
                <x>   0 </x>
                <y>    0.0 </y>
                <z>    -1.0 </z>
            </direction>
        </force>
        <!--ONLY FOR TESTING-->
        <force name="testing3" frame="BODY">
            <location unit="IN">
                <x>72</x>
                <y> -200 </y>
                <z> 0 </z>
            </location>
            <direction>
                <x>   0 </x>
                <y>    0.0 </y>
                <z>    -1.0 </z>
            </direction>
        </force>
        <!--ONLY FOR TESTING-->
        <force name="testing4" frame="BODY">
            <location unit="IN">
                <x>72</x>
                <y> 200 </y>
                <z> 0 </z>
            </location>
            <direction>
                <x>   0 </x>
                <y>    0.0 </y>
                <z>    -1.0 </z>
            </direction>
        </force>



 </external_reactions>

</fdm_config>
