CVS: data/Aircraft/Lockheed-NF104 README.txt, NONE, 1.1 f104-jsbsim-cnf.xml, NONE, 1.1 f104-set.xml, NONE, 1.1 f104.xml, NONE, 1.1 nf104-base.xml, NONE, 1.1 nf104-splash.png, NONE, 1.1 thumbnail.jpg, NONE, 1.1
Emmanuel Baranger <[email protected]>
| Newsgroups | gmane.games.flightgear.cvc |
|---|---|
| Message-ID | <[email protected]> |
Update of /var/cvs/FlightGear-0.9/data/Aircraft/Lockheed-NF104
In directory baron.flightgear.org:/tmp/cvs-serv23742
Added Files:
README.txt f104-jsbsim-cnf.xml f104-set.xml f104.xml
nf104-base.xml nf104-splash.png thumbnail.jpg
Log Message:
- New NF 104 C (by separate NF 104 A and NF 104 C)
--- NEW FILE "README.txt" ---
LOCKHEED F-104C STARFIGHTER, v. 1.2, 10 Feb 2010, released under Creative Commons license CC-BY-NC-SA
CHANGES FROM V. 1.1:
1. Corrects faulty airspeed indication.
2. VVI now uses FDM data for a more instantaneous indication.
ACKNOWLEDGEMENTS:
1. The FDM is my work, derived from the current Aeromatic program.
2. The airframe 3D is based on Emmanual Baranger's NF-104A (released under GNU General Public License v. 2).
3. Polished metal and tire-smoke effects are based on A.J. MacLeod's BAC Lightning F1.A (released under GNU General Public License v. 2).
3. Pilot and afterburner nozzle/flame 3Ds are based on Gerard Robin's SR-71 (released under GNU General Public License v. 2).
4. Gun effects and submodels/systems are based on David Culp's work (released under Creative Commons license CC-BY-NC-SA), with the exception of the M61.wav, which was freeware from SoundBible.com that I edited.
NOTE: This has been removed from the CVS version. For the full version see:
http://home.comcast.net/~davidculp2/hangar/hangar.html
5. If you recognize your work in this model and I haven't acknowledged it, it's because of my oversight rather than intent. Please e-mail me at [email protected] and point out my error. I'll attribute you here.
INSTRUMENTATION NOTES (TOGGLE CONTROL-C FOR PANEL LOCATIONS):
-- Attitude Indicator: Includes horizon adjust click panels on each side of the knob. Click the knob itself to reset to zero.
-- Auto ILS (control-i): For the lazy among us, flies localizer, glide slope, and airspeed. You need to be in the reasonable vicinity of all three before you activate the function.
-- Autopilot: Retuned version of the FlightGear generic autopilot for better responsiveness to fighter aircraft.
-- Altimeter:
Local Weather Fetch Enabled: Using a Nasal aplet, automatically sets local barometric pressure below 18,000 feet and 29.92, the standard datum plane for pressure altitude in the United States, above 18,000 feet (change-over altitude is different elsewhere). Indicated altitude is local below 18,000 feet and pressure altitude above 18,000 feet. The autopilot uses indicated altitude for computations.
Local Weather Fetch Disabled: Pilot sets manually, and autopilot uses indicated altitude for computations.
-- Approach Speed Indicator: Using a Nasal aplet, a small triangle on the outside edge of the airspeed face automatically indicates approach speed (170 KIAS plus 5 KIAS for every 1000 pounds of fuel over 1000 pounds). Just control your airspeed to keep the needle on the approach speed indicator.
-- External stores (tip tank) jettison and arrestor hook release buttons are clickable in the cockpit.
-- Light Panel: On the right console at the 3 o'clock position.
-- Radar: Currently displays only the tanker and a 20-mile range.
-- Radio Direction Magnetic Indicator (RDMI): Displays both TACAN (wide needle) and VOR (narrow needle).
-- Refueling: Probe capable with KA-6D (refueling_demo_2 in FlightGear).
--- NEW FILE "f104-jsbsim-cnf.xml" ---
<?xml version="1.0" encoding="UTF-8"?>
<!--
************************************************************************
Lockheed NF 104 simulation config.
2008-08-08 Erik Hofman
************************************************************************
-->
<PropertyList include="nf104-base.xml">
<sim>
<description>Lockheed F 104C (JSBSim)</description>
<flight-model>jsb</flight-model>
<aero>f104</aero>
</sim>
</PropertyList>
--- NEW FILE "f104-set.xml" ---
<?xml version="1.0" encoding="UTF-8"?>
<PropertyList include="f104-jsbsim-cnf.xml">
<sim>
<description>Lockheed F-104</description>
<author>Erik Hofman (FDM), Emmanuel BARANGER, Kent Esbenshade (3D)</author>
<!--
<model>
<path>Aircraft/Lockheed-NF104/Models/F-104C.xml</path>
<livery>
<file type="string">default</file>
</livery>
</model>
-->
</sim>
<nasal>
<Lockheed-NF104>
<file>Aircraft/Lockheed-NF104/Nasal/tire-rotation.nas</file>
<file>Aircraft/Lockheed-NF104/Nasal/tire-smoke.nas</file>
</Lockheed-NF104>
</nasal>
<fdm>
<jsbsim>
<systems>
<canopy>
<command type="double">0</command>
<position type="double">0</position>
</canopy>
<NWS>
<engaged type="double">0</engaged>
</NWS>
<radar>
<range type="int">40</range>
</radar>
<tailhook>
<tailhook-cmd-norm type="double">0</tailhook-cmd-norm>
</tailhook>
</systems>
</jsbsim>
</fdm>
</PropertyList>
--- NEW FILE "f104.xml" ---
<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="F-104C" version="2.0" release="ALPHA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> Aeromatic v 0.91 </author>
<filecreationdate> 2009-08-14 </filecreationdate>
<version>$Revision: 1.1 $</version>
<description>Models an F-104C</description>
</fileheader>
<!--
File: F-104C-jsbsim.xml
Inputs:
name: F-104C
type: single-engine transonic/supersonic fighter
max weight: 27855 lb
wing span: 21.94 ft
length: 54.77 ft
wing area: 196.1 sq-ft
gear type: tricycle
retractable?: yes
# engines: 1
engine type: turbine
engine layout: aft fuselage
yaw damper? yes
Outputs:
wing loading: 105 lb/sq-ft
CL-alpha: 3.5 per radian
CL-0: 0.08
CL-max: 1
CD-0: 0.021
K: 0.12
-->
<!--
Note:
All tables that contain data due to Mach 0.257 and 1.8 are taken from Roskam
-->
<metrics>
<wingarea unit="FT2">196.10</wingarea>
<wingspan unit="FT" >21.94</wingspan>
<wing_incidence>0</wing_incidence>
<chord unit="FT" >9.55</chord>
<htailarea unit="FT2">48.20</htailarea>
<htailarm unit="FT" > 46.86</htailarm>
<vtailarea unit="FT2">43.70</vtailarea>
<vtailarm unit="FT" >23.23</vtailarm>
<location name="AERORP" unit="IN">
<x>319.5</x>
<y>0.0</y>
<z>-35.08</z>
</location>
<location name="EYEPOINT" unit="IN">
<x>143</x>
<y>0.0</y>
<z>-4.25</z>
</location>
<location name="VRP" unit="IN">
<x>319.5</x>
<y>0.0</y>
<z>-35.08</z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2">3663</ixx>
<iyy unit="SLUG*FT2">59000</iyy> <!-- orig: 38362, Rk: 59000 -->
<izz unit="SLUG*FT2">60000</izz> <!-- orig: 24572, Rk: 60000 -->
<ixy unit="SLUG*FT2">0</ixy>
<ixz unit="SLUG*FT2">0</ixz>
<iyz unit="SLUG*FT2">0</iyz>
<emptywt unit="LBS" >12760</emptywt>
<location name="CG" unit="IN">
<x>319.5</x>
<y>0.0</y>
<z>-35.08</z>
</location>
<pointmass name="left-tip-tank"><!--empty-->
<weight unit="LBS">125</weight>
<location name="POINTMASS" unit="IN">
<x>389</x>
<y>-148</y>
<z>-52</z>
</location>
</pointmass>
<pointmass name="right-tip-tank"><!--empty-->
<weight unit="LBS">125</weight>
<location name="POINTMASS" unit="IN">
<x>389</x>
<y>148</y>
<z>-52</z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<location unit="IN">
<x>213</x>
<y>0.0</y>
<z>-132</z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 6723.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2241.00 </damping_coeff>
<max_steer unit="DEG">60.00</max_steer>
<brake_group>NONE</brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MAIN">
<location unit="IN">
<x>393.6</x>
<y>-63.20</y>
<z>-121</z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 22410.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4482.00 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>LEFT</brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MAIN">
<location unit="IN">
<x>393.6</x>
<y>63.20</y>
<z>-121</z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 22410.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4482.00 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>RIGHT</brake_group>
<retractable>1</retractable>
</contact>
<contact type="STRUCTURE" name="NOSE">
<location unit="IN">
<x>0</x>
<y>0</y>
<z>-43</z>
</location>
<static_friction>0.80</static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 22410.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4482.00 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="TAIL">
<location unit="IN">
<x>656</x>
<y>0</y>
<z>-2.5</z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 22410.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4482.00 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="LEFT_WING">
<location unit="IN">
<x>422.4</x>
<y>-166.5</y>
<z>-54.6</z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 22410.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4482.00 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_WING">
<location unit="IN">
<x>422.4</x>
<y>166.5</y>
<z>-54.6</z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 22410.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4482.00 </damping_coeff>
</contact>
</ground_reactions>
<propulsion>
<engine file="J79-GE-11A">
<location unit="IN">
<x>342.06</x>
<y>0.00</y>
<z>-23.29</z>
</location>
<orient unit="DEG">
<pitch>0.0</pitch>
<roll>0.0</roll>
<yaw>0.0</yaw>
</orient>
<feed>0</feed>
<feed>1</feed>
<feed>2</feed>
<thruster file="direct">
<location unit="IN">
<x>622.05</x>
<y>0.00</y>
<z>-23.29</z>
</location>
<orient unit="DEG">
<pitch>0.0</pitch>
<roll>0.0</roll>
<yaw>0.0</yaw>
</orient>
</thruster>
</engine>
<!--internal-->
<tank type="FUEL" number="0">
<location unit="IN">
<x>319.5</x>
<y>0.0</y>
<z>-35.08</z>
</location>
<capacity unit="LBS">6050.00</capacity>
<contents unit="LBS">5000.00</contents>
</tank>
<!--left tip tank-->
<tank type="FUEL" number="1">
<location unit="IN">
<x>389</x>
<y>-148</y>
<z>-52</z>
</location>
<capacity unit="LBS">1400.00</capacity>
<contents unit="LBS">1000.00</contents>
</tank>
<!--right tip tank-->
<tank type="FUEL" number="2">
<location unit="IN">
<x>389</x>
<y>148</y>
<z>-52</z>
</location>
<capacity unit="LBS">1400.00</capacity>
<contents unit="LBS">1000.00</contents>
</tank>
</propulsion>
<system file="armament"/>
<system file="beacon"/>
<system file="BLC"/>
<system file="canopy"/>
<system file="chute"/>
<system file="crash-detect"/>
<system file="FCS-pitch"/>
<system file="FCS-roll"/>
<system file="FCS-yaw"/>
<system file="flaps"/>
<system file="gear"/>
<system file="NWS"/>
<system file="radar"/>
<system file="speedbrakes"/>
<system file="tailhook"/>
<flight_control name="FCS"></flight_control>
<aerodynamics>
<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 1.2290
0.1000 1.1240
0.1500 1.1160
0.2000 1.1240
0.3000 1.1050
0.4000 1.0410
0.5000 1.0340
0.6000 1.0190
0.7000 1.0080
0.8000 1.0030
0.9000 1.0010
1.0000 1.0000
1.1000 1.0000
</tableData>
</table>
</product>
</function>
<axis name="LIFT">
<function name="aero/coefficient/CLo">
<description>Lift_at_zero_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.4000 0.0100
0.6000 0.0100
0.8000 0.0100
0.9000 0.0100
1.0000 -0.0100
1.2000 -0.0200
1.4000 0.0400
1.6000 0.0320
1.8000 0.0200
2.0000 0.0100
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLalpha">
<description>Lift_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/alpha-rad</property>
<property>velocities/mach</property>
<property>aero/function/kCLge</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.4000 7.1154
0.6000 4.8432
0.8000 4.2637
0.9000 4.3529
1.0000 4.2055
1.2000 3.1401
1.4000 2.2916
1.6000 1.7603
1.8000 1.3831
2.0000 1.1042
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLDf">
<description>Delta_lift_due_to_flap_deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 7.0000 13.0000
0.6500 0.0000 0.0890 0.4000
0.7000 0.0000 0.0890 0.3810
0.7500 0.0000 0.0990 0.3410
0.8000 0.0000 0.1080 0.3520
0.8500 0.0000 0.1280 0.3460
0.9000 0.0000 0.1380 0.1390
0.9500 0.0000 0.1280 0.2900
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLDh">
<description>Lift_due_to_Horizontal_tail_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.6800
1.8000 0.5200
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLq">
<description>Lift_due_to_pitch_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>velocities/q-aero-rad_sec</property>
<property>aero/ci2vel</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 2.3000
1.8000 1.9000
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLadot">
<description>Lift_due_to_alpha_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/alphadot-rad_sec</property>
<property>aero/ci2vel</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.6600
1.8000 0.8200
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/dCLslat">
<description>Delta_Lift_due_to_slats</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">fcs/flap-pos-norm</independentVar>
<tableData>
0.00 0.025
0.30 0.125
1.00 0.25
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLBLC">
<description>Delta_Lift_due_to_BLC</description>
<product>
<property>systems/BLC/active</property>
<value> 0.2 </value>
</product>
</function>
<function name="aero/coefficient/dCLsb">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0</value>
</product>
</function>
</axis>
<axis name="DRAG">
<function name="aero/coefficient/CDo">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 0.0160
0.8000 0.0160
0.8500 0.0163
0.8800 0.0170
0.9000 0.0170
0.9250 0.0190
0.9500 0.0230
0.9750 0.0310
1.0000 0.0380
1.0500 0.0470
1.1000 0.0500
1.1500 0.0500
1.2000 0.0490
1.4000 0.0468
1.6000 0.0440
1.8000 0.0430
2.0000 0.0422
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDalpha">
<description>Drag_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">velocities/mach</independentVar>
<tableData>
0.0000 0.8000 0.9000 1.0000 1.2000 1.4000 1.6000 1.8000 2.0000
-0.0700 0.0034 0.0049 0.0059 0.0093 0.0109 0.0040 0.0035 0.0042 0.0041
-0.0350 0.0010 0.0013 0.0015 0.0026 0.0032 0.0010 0.0011 0.0017 0.0018
0.0000 0.0002 0.0002 0.0001 0.0002 0.0006 0.0011 0.0010 0.0008 0.0004
0.0350 0.0024 0.0022 0.0031 0.0036 0.0046 0.0072 0.0059 0.0052 0.0037
0.0700 0.0093 0.0118 0.0165 0.0195 0.0187 0.0243 0.0198 0.0161 0.0133
0.1050 0.0240 0.0332 0.0465 0.0472 0.0425 0.0506 0.0430 0.0345 0.0176
0.1400 0.0465 0.0589 0.0822 0.0860 0.0788 0.0837 0.0722 0.0593 0.0479
0.1750 0.0703 0.0851 0.1361 0.1674 0.1298 0.1257 0.1052 0.0894 0.0741
0.2090 0.1074 0.1205 0.1988 0.3273 0.2195 0.1945 0.1487 0.1220 0.1013
0.2440 0.1679 0.1684 0.2999 0.6122 0.3791 0.3195 0.1529 0.1650 0.1331
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDbeta">
<description>Drag_due_to_sideslip</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/beta-rad</independentVar>
<tableData>
-1.57 1.230
-0.26 0.050
0.00 0.000
0.26 0.050
1.57 1.230
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDdh">
<description>Drag_due_to_Elevator_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<abs><property>fcs/elevator-pos-norm</property></abs>
<value>0.04</value>
</product>
</function>
<function name="aero/coefficient/CDgear">
<description>Drag_due_to_landing_gear</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>gear/gear-pos-norm</independentVar>
<tableData>
0.0000 0.0000
0.3000 0.1000
1.0000 0.0600
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDflap">
<description>Drag_due_to_flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/flap-pos-norm</property>
<value>0.002679</value>
</product>
</function>
<function name="aero/coefficient/CDslat">
<description>Drag_due_to_slats</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">fcs/flap-pos-norm</independentVar>
<tableData>
0.00 0.003
0.30 0.015
1.00 0.03
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDbc">
<description>Drag_due_to_braking_chute</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>systems/chute/unfurl-norm</property>
<value>.75</value>
</product>
</function>
<function name="aero/coefficient/CDsb">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0.04</value>
</product>
</function>
</axis>
<axis name="SIDE">
<function name="aero/coefficient/CYb">
<description>Side_force_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/beta-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -1.1800
1.8000 -1.0450
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CYDr">
<description>Side_force_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rudder-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.3290
1.8000 0.0870
</tableData>
</table>
</product>
</function>
</axis>
<axis name="ROLL">
<function name="aero/coefficient/Clb">
<description>Roll_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -0.1750
1.8000 -0.0930
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Clp">
<description>Roll_moment_due_to_roll_rate_(roll_damping)</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-rad_sec</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -0.2850
1.8000 -0.2720
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Clr">
<description>Roll_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-rad_sec</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.2650
1.8000 0.1540
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/ClDa">
<description>Roll_moment_due_to_aileron</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.0392
1.8000 0.0173
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/ClDr">
<description>Roll_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.0448
1.8000 0.0079
</tableData>
</table>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/coefficient/Cmalpha">
<description>Pitch_moment_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/alpha-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -0.6440
1.8000 -1.3080
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmo">
<description>Pitching_moment_at_zero_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.0300
1.8000 -0.0280
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmde">
<description>Pitch_moment_due_to_elevator</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elevator-pos-rad</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.0 -0.800
2.0 -0.200
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmq">
<description>Pitch_moment_due_to_pitch_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>velocities/q-rad_sec</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -5.84
1.8000 -4.83
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmadot">
<description>Pitch_moment_due_to_alpha_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>aero/alphadot-rad_sec</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -1.6400
1.8000 -2.0500
</tableData>
</table>
</product>
</function>
</axis>
<axis name="YAW">
<function name="aero/coefficient/Cnb">
<description>Yaw_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.5070
1.8000 0.2420
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cnp">
<description>Yaw_moment_due_to_roll_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-rad_sec</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -0.1440
1.8000 -0.0930
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cnr">
<description>Yaw_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-rad_sec</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -0.7530
1.8000 -0.6490
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CnDr">
<description>Yaw_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -0.1645
1.8000 -0.0435
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CnDa">
<description>Yaw_moment_due_to_aileron</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.0042
1.8000 0.0025
</tableData>
</table>
</product>
</function>
</axis>
</aerodynamics>
</fdm_config>
--- NEW FILE "nf104-base.xml" ---
<?xml version="1.0" encoding="UTF-8"?>
<PropertyList>
<sim include="Nasal/views.xml">
<author>BARANGER Emmanuel</author>
<aircraft-version>0.2</aircraft-version>
<status>0.1 Alpha</status>
<fuel-fraction>0.75</fuel-fraction>
<startup>
<splash-texture>Aircraft/Lockheed-NF104/nf104-splash.png</splash-texture>
</startup>
<sound>
<path>Aircraft/Lockheed-NF104/Sounds/nf104-sound.xml</path>
</sound>
<model>
<path>Aircraft/Lockheed-NF104/Models/F-104C.xml</path>
<livery>
<file type="string">default</file>
</livery>
</model>
<virtual-cockpit archive="y">true</virtual-cockpit>
<allow-toggle-cockpit archive="y">true</allow-toggle-cockpit>
<multiplay>
<chat_display>1</chat_display>
</multiplay>
<!-- Flap settings -->
<flaps>
<setting>0</setting>
<setting>0.3</setting>
<setting>1</setting>
</flaps>
<weight n="0">
<name>Crew</name>
<weight-lb>180</weight-lb>
<max-lb>400</max-lb>
<min-lb>180</min-lb>
</weight>
<help>
<title>Convair F 106 Delta Dart</title>
<key>
<name>d</name>
<desc>Open/Close canopy</desc>
</key>
</help>
<replay>
<disable>1</disable>
</replay>
<menubar include="Dialogs/nf104-menu.xml"/>
</sim>
<environment>
<turbulence>
<use-cloud-turbulence>true</use-cloud-turbulence>
</turbulence>
</environment>
<engines>
<engine n="0">
<engine-num type="int">0</engine-num>
<running>true</running>
</engine>
</engines>
<consumables>
<fuel>
<tank n="0">
<tank-num type="int">0</tank-num>
<level-gal_us archive="y">2070</level-gal_us>
</tank>
</fuel>
</consumables>
<input>
<keyboard include="Nasal/nf104-keyboard.xml"/>
</input>
</PropertyList>
--- NEW BINARY FILE "nf104-splash.png" ---
--- NEW BINARY FILE "thumbnail.jpg" ---
------------------------------------------------------------------------------
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