diff --git a/aircraft/EasyStar/EasyStar-datcom-set.xml b/aircraft/EasyStar/EasyStar-datcom-set.xml new file mode 100644 index 0000000000000000000000000000000000000000..32d5786963b136c4906138d591cc308362bb1aa0 --- /dev/null +++ b/aircraft/EasyStar/EasyStar-datcom-set.xml @@ -0,0 +1,20 @@ +<?xml version="1.0"?> +<PropertyList xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xsi:noNamespaceSchemaLocation="../../XMLSchemas/PropertyList.xsd"> + <sim> + <author>James Goppert</author> + <description>Multiplex Easy Star (DATCOM)</description> + <aircraft-version>0.0.0</aircraft-version> + <status>early-production</status> + <startup> + <splash-title>Multiplex Easy Star</splash-title> + </startup> + <model> + <path>Aircraft/EasyStar/Models/EasyStar-model.xml</path> + </model> + <sound> + <path>Aircraft/EasyStar/EasyStar-sound.xml</path> + </sound> + <flight-model>jsb</flight-model> + <aero>EasyStar-datcom</aero> + </sim> +</PropertyList> diff --git a/aircraft/EasyStar/EasyStar-datcom.xml b/aircraft/EasyStar/EasyStar-datcom.xml new file mode 100644 index 0000000000000000000000000000000000000000..3f91cb2a3b077f87c3d7b94c6fd26b46aea03468 --- /dev/null +++ b/aircraft/EasyStar/EasyStar-datcom.xml @@ -0,0 +1,1372 @@ +<?xml version="1.0"?> +<!-- + This is the JSBSim config file for a PA34-200T SenecaII. + The aerodynamics sections was generated by datcom using + as much real input as available. + + Changes from datcom.xml + + - function attribute NAME must be lowercase + - missing function Delta_lift_due_to_flap_deflection in axis LIFT + - missing function Lift_due_to_Elevator_Deflection in axis LIFT +--> +<?xml-stylesheet href="JSBSim.xsl" type="application/xml"?> +<fdm_config xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" + xsi:noNamespaceSchemaLocation="file:/home/torsten/FlightGear/Aircraft/SenecaII/JSBSim.xsd" + name="EasyStar-datcom" version="2.0" release="BETA"> + + <fileheader> + <author>James Goppert</author> + <filecreationdate>2010-6-3</filecreationdate> + <description>Multiplex Easy Star (DATCOM)</description> + <reference title="Multiplex Easy Star (DATCOM)"/> + </fileheader> + + <!-- ********************************************************************** + METRICS + ********************************************************************** --> + <metrics> + <wingarea unit="FT2"> 2.2792 </wingarea> + <wingspan unit="FT"> 4.5000 </wingspan> + <chord unit="FT"> .5606 </chord> + <htailarea unit="FT2"> .4457 </htailarea> + <htailarm unit="FT"> .4280 </htailarm> + <vtailarea unit="FT2"> .1606 </vtailarea> + <vtailarm unit="FT"> .7127 </vtailarm> + <!-- + the aerodynamic reference point, common point for + aerodynamic forces (lift and drag) + --> + <location name="AERORP" unit="IN"> + <x> 4.0 </x> + <y> 0.0 </y> + <z> 0.0 </z> + </location> + <!-- the eyepoint of the pilot (left or right eye?) --> + <location name="EYEPOINT" unit="IN"> + <x> 0.0 </x> + <y> 0.0 </y> + <z> 0.0 </z> + </location> + <!-- the visual reference point of the 3d model --> + <location name="VRP" unit="IN"> + <x> 0.0 </x> + <y> 0.0 </y> + <z> 0.0 </z> + </location> + </metrics> + + <!-- ********************************************************************** + MASS_BALANCE + ********************************************************************** --> + <mass_balance> + <ixx unit="SLUG*FT2"> .1 </ixx> + <iyy unit="SLUG*FT2"> .1 </iyy> + <izz unit="SLUG*FT2"> .1 </izz> + <ixz unit="SLUG*FT2"> 0 </ixz> + <emptywt unit="LBS"> 2.0 </emptywt> + <!-- the center of gravity --> + <location name="CG" unit="IN"> + <x> 3.0 </x> + <y> 0.0 </y> + <z> 0.0 </z> + </location> + <!--<pointmass name="PAYLOAD">--> + <!--<weight unit="LBS"> 0.0 </weight>--> + <!--<location name="POINTMASS" unit="IN">--> + <!--<x> 39.3 </x>--> + <!--<y> 0 </y>--> + <!--<z> 35.3 </z>--> + <!--</location>--> + <!--</pointmass>--> + </mass_balance> + <!-- ********************************************************************** + UNDERCARRIAGE + ********************************************************************** --> + <ground_reactions> + <contact type="STRUCTURE" name="TAIL_SKID"> + <location unit="IN"> + <x> 27.0 </x> + <y> 0 </y> + <z>-2.0 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + <contact type="STRUCTURE" name="NOSE"> + <location unit="IN"> + <x> -5.0 </x> + <y> 0.0 </y> + <z> 0.0 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + <contact type="STRUCTURE" name="BOTTOM_CANOPY"> + <location unit="IN"> + <x> 0.0 </x> + <y> 0.0 </y> + <z> -3.0 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + + <contact type="STRUCTURE" name="LEFT_WING"> + <location unit="IN"> + <x> -3.0 </x> + <y> -27.5 </y> + <z> 1.0 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + <contact type="STRUCTURE" name="RIGHT_WING"> + <location unit="IN"> + <x> -3.0 </x> + <y> 27.5 </y> + <z> 1.0 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + <contact type="STRUCTURE" name="VERTICAL_TAIL"> + <location unit="IN"> + <x> 27.0 </x> + <y> 0.0 </y> + <z> 6.5 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + <contact type="STRUCTURE" name="CABIN_TOP"> + <location unit="IN"> + <x> 0.0 </x> + <y> 0.0 </y> + <z> 2.0 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + </ground_reactions> + <!-- ********************************************************************** + PROPULSION + ********************************************************************** --> + <propulsion> + <engine file="HB2815-2000"> + <location unit="IN"> + <x> 10.0 </x> + <y> 0 </y> + <z> 3.0 </z> + </location> + <orient unit="DEG"> + <roll> 0.0 </roll> + <pitch> -5 </pitch> + <yaw> 0 </yaw> + </orient> + <feed>0</feed> + <thruster file="apc6x4"> + <location unit="IN"> + <x> 10.0 </x> + <y> 0 </y> + <z> 3.0 </z> + </location> + <orient unit="DEG"> + <roll> 0.0 </roll> + <pitch> -5.0 </pitch> + <yaw> 0.0 </yaw> + </orient> + <p_factor>1.0</p_factor> + </thruster> + </engine> + <!--throws warning if tank not included, no real purpose--> + <tank type="FUEL"> <!-- Tank number 0 --> + <location unit="IN"> + <x> 0.0 </x> + <y> 0.0 </y> + <z> 0.0 </z> + </location> + <capacity unit="LBS"> 0.0001 </capacity> + <contents unit="LBS"> 0 </contents> + </tank> + </propulsion> + <!-- ********************************************************************** + FLIGHT CONTROLS + ********************************************************************** --> + <flight_control name="EasyStar"> + <!-- + Elevator + --> + <channel name="Pitch"> + <summer name="Pitch Trim Sum"> + <input>fcs/elevator-cmd-norm</input> + <input>fcs/pitch-trim-cmd-norm</input> + <clipto> + <min>-1</min> + <max>1</max> + </clipto> + <output>fcs/elevator-pos-norm</output> + </summer> + <aerosurface_scale name="Elevator Control"> + <input>fcs/pitch-trim-sum</input> + <gain>0.01745</gain> + <range> + <min>-28</min> + <max>23</max> + </range> + <output>fcs/elevator-pos-rad</output> + </aerosurface_scale> + </channel> + <!-- + Rudder + --> + <channel name="Yaw"> + <summer name="Yaw Trim Sum"> + <input>fcs/rudder-cmd-norm</input> + <input>fcs/yaw-trim-cmd-norm</input> + <clipto> + <min>-1</min> + <max>1</max> + </clipto> + </summer> + <!--<pure_gain name="Aileron Crossfeed">--> + <!--<input>fcs/aileron-cmd-norm</input>--> + <!--<gain>-1</gain>--> + <!--<output>fcs/rudder-pos-norm</output>--> + <!--</pure_gain>--> + <summer name="Yaw Mix"> + <input>fcs/yaw-trim-sum</input> + <!--<input>fcs/aileron-crossfeed</input>--> + <clipto> + <min>-1</min> + <max>1</max> + </clipto> + </summer> + <aerosurface_scale name="Rudder Control"> + <input>fcs/yaw-mix</input> + <gain>0.01745</gain> + <range> + <min>-27</min> + <max>27</max> + </range> + <output>fcs/rudder-pos-rad</output> + </aerosurface_scale> + </channel> + <!-- + Throttle (linear vs rpm approx.) + --> + <channel name="Throttle"> + <fcs_function name="fcs/rpm-scaled-throttle"> + <function> + <pow> + <property>fcs/throttle-cmd-norm</property> + <value>3</value> + </pow> + </function> + </fcs_function> + <aerosurface_scale name="Throttle Control"> + <input>fcs/rpm-scaled-throttle</input> + <range> + <min>-1</min> + <max>1</max> + </range> + <output>fcs/throttle-pos-norm</output> + </aerosurface_scale> + </channel> + + </flight_control> + +<!-- + + + ****************** IMPORTANT NOTICES ********************** + + This is an alpha version release of the DATCOM+ program for + JSBSIM. Nothing, and I do mean NOTHING, as been checked to + verify that the parameters, units, sign conventions, or + basically anything else is correct. Your mileage may vary. + + *********************************************************** + + This file was generated by the USAF Digital DATCOM program. + This file is considered an intermediary file in the + DATCOM/JSBSim process. This file may be overwritten without + warning, so any changes that you make in here may be lost. + + If you intend to use this file as it is and modify it, make + sure that you take the necessary precautions to prevent it + from being overwritten, like renaming it. + + + *********************************************************** + + + DISCLAIMER REQUIRED BY HQ USAF FOR PUBLIC RELEASE APPROVAL + + THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION + IS RELEASED "AS IS". THE U.S. GOVERNMENT MAKES NO + WARRANTY OF ANY KIND, EXPRESS OR IMPLIED, CONCERNING + THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION, + INCLUDING, WITHOUT LIMITATION, ANY WARRANTIES OF + MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE. + IN NO EVENT WILL THE U.S. GOVERNMENT BE LIABLE FOR ANY + DAMAGES, INCLUDING LOST PROFITS, LOST SAVINGS OR OTHER + INCIDENTAL OR CONSEQUENTIAL DAMAGES ARISING OUT OF THE + USE, OR INABILITY TO USE, THIS SOFTWARE OR ANY + ACCOMPANYING DOCUMENTATION, EVEN IF INFORMED IN ADVANCE + OF THE POSSIBILITY OF SUCH DAMAGES. + + + *********************************************************** +--> + + + + + + + +<!-- ********************************************************************** + AERODYNAMICS + ********************************************************************** +--> + + + <aerodynamics> + + <alphalimits unit="DEG"> + <min> -16.00 </min> + <max> 24.00 </max> + </alphalimits> + + + + + <!-- ************************* + Sign Conventions + ************************* + + Control displacements + Stick FWD + / Aft - + Stick Left + / Right - + Wheel CCW + / CW - + Pedal Left + / Right - + Elevator trim Nose Up + / Nose down - + + Surfaces + Elevator TED + / TEU - + R Ail TED + / TEU - + L Ail TED + / TEU - + Rudder TEL + / TER - + + F&M, Accel, Rates, Displacements + Pitch Up + / Down - + Roll Rgt + / Left - + Yaw Rgt + / Left - + + Other + Alpha Up + / Down - + Beta Wind in right ear + / Wind in left ear - + Slip Ball right of center + / left of center - + --> + + + + + <!-- ************************************** + ASSUMPTIONS AND LIMITATIONS + + There is no interaction between deflected surfaces modeled + so there is no change in elevator effects with the flaps + deflected, for example. + + Terms known to be missing from DATCOM: + Power effects + Ground effects + Cyr, CyDr, Cyda, ClDr, Cndr + + ************************************** + --> + + + <!-- + The following ground effect tables are NOT generated + by DATCOM, but provide representative effects. + These terms are not currently used in this model. + --> + + + <function name="aero/function/ground-effect-factor-lift"> + <description>Change in lift due to ground effect factor</description> + <product> + <table> + <independentVar lookup="row">aero/h_b-mac-ft</independentVar> + <tableData> + 0.0 1.203 + 0.1 1.127 + 0.15 1.090 + 0.2 1.073 + 0.3 1.046 + 0.4 1.055 + 0.5 1.019 + 0.6 1.013 + 0.7 1.008 + 0.8 1.006 + 0.9 1.003 + 1.0 1.002 + 1.1 1.0 + </tableData> + </table> + </product> + </function> + + <function name="aero/function/ground-effect-factor-drag"> + <description>Change in drag due to ground effect</description> + <product> + <table> + <independentVar lookup="row">aero/h_b-mac-ft</independentVar> + <tableData> + 0.0 0.480 + 0.1 0.515 + 0.15 0.629 + 0.2 0.709 + 0.3 0.815 + 0.4 0.882 + 0.5 0.928 + 0.6 0.962 + 0.7 0.988 + 0.8 1.0 + 0.9 1.0 + 1.0 1.0 + 1.1 1.0 + </tableData> + </table> + </product> + </function> + + + + + +<!-- ********************************************************************** --> + + + <axis name="LIFT"> + + + <function name="aero/coefficient/CLwbh"> + <description> + Lift due to alpha + Increase in CL decreases Period and damping,Dutch Roll damping + CL is low for landing + </description> + <product> + <property>aero/function/ground-effect-factor-lift</property> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -1.216 + -8.000 -.4490 + -6.000 -.2713 + -4.000 -.9559E-01 + -2.000 .7950E-01 + .000 .2620 + 2.000 .4513 + 4.000 .6466 + 8.000 1.053 + 9.000 1.157 + 10.00 1.248 + 12.00 1.403 + 14.00 1.529 + 16.00 1.620 + 18.00 1.660 + 19.00 1.659 + 20.00 1.545 + 21.00 1.332 + 22.00 1.097 + 24.00 .8071 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/CLq"> + <description> + Basic Lift Coefficient due to pitch rate(per degree) + </description> + <product> + <property>velocities/q-aero-rad_sec</property> + <value>57.29577951</value> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>aero/ci2vel</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 .1523 + -8.000 .1523 + -6.000 .1523 + -4.000 .1523 + -2.000 .1523 + .000 .1523 + 2.000 .1523 + 4.000 .1523 + 8.000 .1523 + 9.000 .1523 + 10.00 .1523 + 12.00 .1523 + 14.00 .1523 + 16.00 .1523 + 18.00 .1523 + 19.00 .1523 + 20.00 .1523 + 21.00 .1523 + 22.00 .1523 + 24.00 .1523 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/CLad"> + <description> + Basic Lift Coefficient due to AOA rate(per degree) + Important contributor to Short-Period damping + For low Cla, aircraft must land at high alpha + </description> + <product> + <property>aero/alphadot-deg_sec</property> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>aero/ci2vel</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 .3510E-01 + -8.000 .3144E-01 + -6.000 .3313E-01 + -4.000 .3315E-01 + -2.000 .3284E-01 + .000 .3296E-01 + 2.000 .3277E-01 + 4.000 .3230E-01 + 8.000 .2898E-01 + 9.000 .2806E-01 + 10.00 .2572E-01 + 12.00 .1946E-01 + 14.00 .1550E-01 + 16.00 .1016E-01 + 18.00 -.2053E-02 + 19.00 -.1167E-01 + 20.00 -.3353E-01 + 21.00 -.5670E-01 + 22.00 -.5279E-01 + 24.00 -.3183E-01 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/CLDe"> + <description> + Lift Coefficient due to Elevator Deflection + Positive surface deflection is trailing edge down + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <table> + <independentVar lookup="row">fcs/elevator-pos-deg</independentVar> + <tableData> + -20.00 -.6476E-01 + -15.00 -.5856E-01 + -10.00 -.4002E-01 + -5.000 -.2001E-01 + .000 .4002E-04 + 5.000 .2001E-01 + 10.00 .4002E-01 + 13.00 .5157E-01 + 16.00 .6162E-01 + </tableData> + </table> + </product> + </function> + + </axis> + + + + +<!-- ********************************************************************** --> + + + <axis name="DRAG"> + + + <function name="aero/coefficient/CD"> + <description> + Basic Drag Coefficient + Sense: Always positive + Main contributor to Phugoid damping: Greater Cd, Better damping + </description> + <product> + <property>aero/function/ground-effect-factor-lift</property> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 .1667 + -8.000 .4475E-01 + -6.000 .3290E-01 + -4.000 .2639E-01 + -2.000 .2554E-01 + .000 .3065E-01 + 2.000 .4245E-01 + 4.000 .6156E-01 + 8.000 .1232 + 9.000 .1436 + 10.00 .1636 + 12.00 .2014 + 14.00 .2355 + 16.00 .2637 + 18.00 .2813 + 19.00 .2851 + 20.00 .2611 + 21.00 .2185 + 22.00 .1816 + 24.00 .1539 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/CdDe"> + <description> + Drag Coefficient due to Elevator Deflection + Positive surface deflection is trailing edge down + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <independentVar lookup="column">fcs/elevator-pos-deg</independentVar> + <tableData> + -20.00 -15.00 -10.00 -5.000 .000 5.000 10.00 13.00 16.00 + -16.00 .5945E-02 .5210E-02 .3237E-02 .1444E-02 -.2539E-05 -.1095E-02 -.1842E-02 -.2114E-02 -.2256E-02 + -8.000 .3346E-02 .2862E-02 .1633E-02 .6419E-03 -.9344E-06 -.2931E-03 -.2373E-03 -.4624E-04 .2148E-03 + -6.000 .2700E-02 .2278E-02 .1234E-02 .4425E-03 -.5355E-06 -.9363E-04 .1616E-03 .4677E-03 .8290E-03 + -4.000 .2027E-02 .1671E-02 .8186E-03 .2349E-03 -.1202E-06 .1140E-03 .5768E-03 .1003E-02 .1468E-02 + -2.000 .1338E-02 .1048E-02 .3930E-03 .2209E-04 .3054E-06 .3268E-03 .1002E-02 .1551E-02 .2124E-02 + .000 .6550E-03 .4315E-03 -.2832E-04 -.1886E-03 .7268E-06 .5375E-03 .1424E-02 .2094E-02 .2773E-02 + 2.000 -.3080E-04 -.1879E-03 -.4516E-03 -.4002E-03 .1150E-05 .7491E-03 .1847E-02 .2640E-02 .3425E-02 + 4.000 -.7194E-03 -.8099E-03 -.8767E-03 -.6128E-03 .1575E-05 .9616E-03 .2272E-02 .3187E-02 .4079E-02 + 8.000 -.2133E-02 -.2087E-02 -.1749E-02 -.1049E-02 .2448E-05 .1398E-02 .3145E-02 .4312E-02 .5423E-02 + 9.000 -.2513E-02 -.2429E-02 -.1984E-02 -.1166E-02 .2683E-05 .1515E-02 .3379E-02 .4614E-02 .5784E-02 + 10.00 -.2896E-02 -.2776E-02 -.2220E-02 -.1285E-02 .2920E-05 .1633E-02 .3616E-02 .4919E-02 .6148E-02 + 12.00 -.3763E-02 -.3559E-02 -.2755E-02 -.1552E-02 .3453E-05 .1901E-02 .4151E-02 .5608E-02 .6972E-02 + 14.00 -.4698E-02 -.4403E-02 -.3333E-02 -.1841E-02 .4031E-05 .2190E-02 .4728E-02 .6352E-02 .7861E-02 + 16.00 -.5692E-02 -.5301E-02 -.3946E-02 -.2148E-02 .4650E-05 .2496E-02 .5342E-02 .7143E-02 .8806E-02 + 18.00 -.6799E-02 -.6301E-02 -.4629E-02 -.2489E-02 .5328E-05 .2838E-02 .6025E-02 .8023E-02 .9858E-02 + 19.00 -.7457E-02 -.6895E-02 -.5036E-02 -.2692E-02 .5729E-05 .3041E-02 .6431E-02 .8547E-02 .1048E-01 + 20.00 -.8200E-02 -.7566E-02 -.5494E-02 -.2921E-02 .6195E-05 .3270E-02 .6889E-02 .9137E-02 .1119E-01 + 21.00 -.9209E-02 -.8478E-02 -.6117E-02 -.3233E-02 .6812E-05 .3582E-02 .7512E-02 .9940E-02 .1215E-01 + 22.00 -.1032E-01 -.9484E-02 -.6805E-02 -.3577E-02 .7499E-05 .3926E-02 .8201E-02 .1083E-01 .1321E-01 + 24.00 -.1205E-01 -.1104E-01 -.7870E-02 -.4109E-02 .8561E-05 .4458E-02 .9265E-02 .1220E-01 .1485E-01 + </tableData> + </table> + </product> + </function> + + </axis> + + + + +<!-- ********************************************************************** --> + + + <axis name="SIDE"> + + + <function name="aero/coefficient/Cyb"> + <description> + Side Force coefficient due to Sideslip(per degree) + Contributes to damping of Dutch Roll mode + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>aero/beta-deg</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.3898E-02 + -8.000 -.3898E-02 + -6.000 -.3898E-02 + -4.000 -.3898E-02 + -2.000 -.3898E-02 + .000 -.3898E-02 + 2.000 -.3898E-02 + 4.000 -.3898E-02 + 8.000 -.3898E-02 + 9.000 -.3898E-02 + 10.00 -.3898E-02 + 12.00 -.3898E-02 + 14.00 -.3898E-02 + 16.00 -.3898E-02 + 18.00 -.3898E-02 + 19.00 -.3898E-02 + 20.00 -.3898E-02 + 21.00 -.3898E-02 + 22.00 -.3898E-02 + 24.00 -.3898E-02 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/Cyp"> + <description> + Side Force Coefficient due to Roll Rate(per degree) + </description> + <product> + <property>velocities/p-aero-rad_sec</property> + <value>57.29577951</value> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>aero/bi2vel</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.6446E-03 + -8.000 -.1072E-02 + -6.000 -.1171E-02 + -4.000 -.1268E-02 + -2.000 -.1364E-02 + .000 -.1460E-02 + 2.000 -.1555E-02 + 4.000 -.1651E-02 + 8.000 -.1855E-02 + 9.000 -.1955E-02 + 10.00 -.2099E-02 + 12.00 -.2372E-02 + 14.00 -.2653E-02 + 16.00 -.3034E-02 + 18.00 -.3638E-02 + 19.00 -.1454E-01 + 20.00 -.5140E-03 + 21.00 -.1285E-02 + 22.00 -.1322E-02 + 24.00 -.1076E-02 + </tableData> + </table> + </product> + </function> + + + <!-- ************************* + Not calculated by DATCOM+ + ************************* + --> + + <function name="aero/coefficient/Cyr"> + <description> + Side Force due to Yaw Rate(DATCOM does not calculate) + Effect is small + </description> + <product> + <property>velocities/r-aero-rad_sec</property> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>aero/bi2vel</property> + <value> .000 </value> + </product> + </function> + + + <!-- ************************* + Not calculated by DATCOM+ + ************************* + --> + + <function name="aero/coefficient/CyDr"> + <description> + Side Force due to rudder(DATCOM does not calculate) + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>fcs/rudder-pos-deg</property> + <value> .000 </value> + </product> + </function> + + + <!-- ************************* + Not calculated by DATCOM+ + ************************* + --> + + <function name="aero/coefficient/CyDa"> + <description> + Side Force due to aileron(DATCOM does not calculate) + Usually neglected + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>fcs/left-aileron-pos-deg</property> + <value> .000 </value> + </product> + </function> + + </axis> + + + + +<!-- ********************************************************************** --> + + + <axis name="ROLL"> + + + <function name="aero/coefficient/Clb"> + <description> + Roll Moment coefficient due to Beta(per degree) + Decrease of Clb to small negative value improves Dutch Roll Damping + High Positive value leads to excessive spiral instability + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>aero/beta-deg</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.1224E-02 + -8.000 -.1221E-02 + -6.000 -.1219E-02 + -4.000 -.1216E-02 + -2.000 -.1212E-02 + .000 -.1208E-02 + 2.000 -.1206E-02 + 4.000 -.1204E-02 + 8.000 -.1203E-02 + 9.000 -.1204E-02 + 10.00 -.1202E-02 + 12.00 -.1194E-02 + 14.00 -.1181E-02 + 16.00 -.1162E-02 + 18.00 -.1134E-02 + 19.00 -.1116E-02 + 20.00 -.1082E-02 + 21.00 -.1034E-02 + 22.00 -.9825E-03 + 24.00 -.9008E-03 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/Clp"> + <description> + Roll Moment coefficient due to roll rate(per degree) + Clp alone determines damping-in-roll characteristics + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>aero/bi2vel</property> + <property>velocities/p-aero-rad_sec</property> + <!--Manually increased roll damping, problem with datcom?--> + <value>-0.5</value> + <!--<table>--> + <!--<independentVar lookup="row">aero/alpha-deg</independentVar>--> + <!--<tableData>--> + <!---16.00 -.7650E-02--> + <!---8.000 -.7063E-02--> + <!---6.000 -.6859E-02--> + <!---4.000 -.6653E-02--> + <!---2.000 -.6738E-02--> + <!--.000 -.7039E-02--> + <!--2.000 -.7303E-02--> + <!--4.000 -.7498E-02--> + <!--8.000 -.7737E-02--> + <!--9.000 -.7239E-02--> + <!--10.00 -.6298E-02--> + <!--12.00 -.4816E-02--> + <!--14.00 -.3420E-02--> + <!--16.00 -.1548E-02--> + <!--18.00 .8581E-03--> + <!--19.00 .5957E-02--> + <!--20.00 .1465E-01--> + <!--21.00 .1964E-01--> + <!--22.00 .1776E-01--> + <!--24.00 .7247E-02--> + <!--</tableData>--> + <!--</table>--> + </product> + </function> + + <function name="aero/coefficient/Clr"> + <description> + Roll Moment coefficient due to yaw rate(per degree) + Considerable effect on Spiral mode. Large + positive values leads to strong sprial instability. + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>aero/bi2vel</property> + <property>velocities/r-aero-rad_sec</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.3497E-02 + -8.000 -.1073E-02 + -6.000 -.4976E-03 + -4.000 .5472E-04 + -2.000 .5948E-03 + .000 .1162E-02 + 2.000 .1754E-02 + 4.000 .2366E-02 + 8.000 .3626E-02 + 9.000 .3944E-02 + 10.00 .4217E-02 + 12.00 .4651E-02 + 14.00 .4975E-02 + 16.00 .5166E-02 + 18.00 .5164E-02 + 19.00 .5079E-02 + 20.00 .4606E-02 + 21.00 .3766E-02 + 22.00 .2861E-02 + 24.00 .1748E-02 + </tableData> + </table> + </product> + </function> + + + <!-- ************************* + Not calculated by DATCOM+ + ************************* + --> + + <function name="aero/coefficient/ClDr"> + <description> + Roll moment due to rudder(DATCOM does not calculate) + Usually insignificant in dynamic stability considerations + but is used in autopilot work + </description> + <product> + <property>metrics/bw-ft</property> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>fcs/rudder-pos-deg</property> + <value> .000 </value> + </product> + </function> + + </axis> + + + + +<!-- ********************************************************************** --> + + + <axis name="PITCH"> + + + <function name="aero/coefficient/Cm_basic"> + <description> + Basic_Pitch_moment_coefficient + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/cbarw-ft</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 .6261 + -8.000 .2937 + -6.000 .2325 + -4.000 .1590 + -2.000 .7771E-01 + .000 -.5162E-02 + 2.000 -.9019E-01 + 4.000 -.1784 + 8.000 -.3681 + 9.000 -.4190 + 10.00 -.4685 + 12.00 -.5701 + 14.00 -.6714 + 16.00 -.7712 + 18.00 .000 + 19.00 .000 + 20.00 .000 + 21.00 .000 + 22.00 .000 + 24.00 .000 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/Cmq"> + <description> + Pitch moment coefficient due to pitch rate(per degree) + Pitch Damping Derivative + Very important to Short Period damping of oscillations + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/cbarw-ft</property> + <property>aero/ci2vel</property> + <property>velocities/q-aero-rad_sec</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.2485 + -8.000 -.2485 + -6.000 -.2485 + -4.000 -.2485 + -2.000 -.2485 + .000 -.2485 + 2.000 -.2485 + 4.000 -.2485 + 8.000 -.2485 + 9.000 -.2485 + 10.00 -.2485 + 12.00 -.2485 + 14.00 -.2485 + 16.00 -.2485 + 18.00 -.2485 + 19.00 -.2485 + 20.00 -.2485 + 21.00 -.2485 + 22.00 -.2485 + 24.00 -.2485 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/Cmadot"> + <description> + Pitch moment coefficient due to AOA rate(per degree) + Negitive Cmad increase Short Period damping + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/cbarw-ft</property> + <property>aero/ci2vel</property> + <property>aero/alphadot-deg_sec</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.1061 + -8.000 -.9502E-01 + -6.000 -.1001 + -4.000 -.1002 + -2.000 -.9926E-01 + .000 -.9960E-01 + 2.000 -.9904E-01 + 4.000 -.9762E-01 + 8.000 -.8757E-01 + 9.000 -.8480E-01 + 10.00 -.7772E-01 + 12.00 -.5882E-01 + 14.00 -.4683E-01 + 16.00 -.3071E-01 + 18.00 .6206E-02 + 19.00 .3526E-01 + 20.00 .1013 + 21.00 .1714 + 22.00 .1595 + 24.00 .9619E-01 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/CmDe"> + <description> + Pitch moment coefficient due to elevator deflection + Positive surface deflection is trailing edge down + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/cbarw-ft</property> + <table> + <independentVar lookup="row">fcs/elevator-pos-deg</independentVar> + <tableData> + -20.00 .2086 + -15.00 .1871 + -10.00 .1282 + -5.000 .6409E-01 + .000 -.1282E-03 + 5.000 -.6409E-01 + 10.00 -.1282 + 13.00 -.1648 + 16.00 -.1970 + </tableData> + </table> + </product> + </function> + + </axis> + + + + +<!-- ********************************************************************** --> + + + <axis name="YAW"> + + + <function name="aero/coefficient/Cnb"> + <description> + Yaw moment coefficient due to sideslip(per degree) + Determines Dutch Roll and Spiral characteristics + Prevents side-slip and yawing moments + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>aero/beta-deg</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 .6403E-03 + -8.000 .6403E-03 + -6.000 .6403E-03 + -4.000 .6403E-03 + -2.000 .6403E-03 + .000 .6403E-03 + 2.000 .6403E-03 + 4.000 .6403E-03 + 8.000 .6403E-03 + 9.000 .6403E-03 + 10.00 .6403E-03 + 12.00 .6403E-03 + 14.00 .6403E-03 + 16.00 .6403E-03 + 18.00 .6403E-03 + 19.00 .6403E-03 + 20.00 .6403E-03 + 21.00 .6403E-03 + 22.00 .6403E-03 + 24.00 .6403E-03 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/Cnp"> + <description> + Yaw moment coefficient due to roll rate(per degree) + Reduces Dutch Roll damping + positive value desireable + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>aero/bi2vel</property> + <property>velocities/p-aero-rad_sec</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 .2909E-03 + -8.000 .1580E-03 + -6.000 .1150E-03 + -4.000 .5960E-04 + -2.000 .8267E-06 + .000 -.4457E-04 + 2.000 -.7403E-04 + 4.000 -.9603E-04 + 8.000 -.1448E-03 + 9.000 -.2952E-03 + 10.00 -.5744E-03 + 12.00 -.1081E-02 + 14.00 -.1590E-02 + 16.00 -.2209E-02 + 18.00 -.2839E-02 + 19.00 -.1963E-02 + 20.00 -.6663E-02 + 21.00 -.6409E-02 + 22.00 -.4810E-02 + 24.00 -.2047E-02 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/Cnr"> + <description> + Yaw Moment coefficient due to yaw rate(per degree) + Main contributor to damping of Dutch Roll + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>aero/bi2vel</property> + <property>velocities/r-aero-rad_sec</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.8275E-03 + -8.000 -.7745E-03 + -6.000 -.7758E-03 + -4.000 -.7821E-03 + -2.000 -.7927E-03 + .000 -.8079E-03 + 2.000 -.8285E-03 + 4.000 -.8551E-03 + 8.000 -.9275E-03 + 9.000 -.9496E-03 + 10.00 -.9698E-03 + 12.00 -.1004E-02 + 14.00 -.1030E-02 + 16.00 -.1043E-02 + 18.00 -.1037E-02 + 19.00 -.1026E-02 + 20.00 -.9793E-03 + 21.00 -.9093E-03 + 22.00 -.8479E-03 + 24.00 -.7868E-03 + </tableData> + </table> + </product> + </function> + + + <!-- ****************************************************** + CnDr is not calculated by DATCOM+, but a default value + is supplied + ******************************************************--> + + <function name="aero/coefficient/CnDr"> + <description> + Yaw Coefficient due to rudder(DATCOM does not calculate) + High value for controllablity, low value + for good dynamic stability + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>fcs/rudder-pos-deg</property> + <value> -.1047E-02</value> + </product> + </function> + + + </axis> + + + + +<!-- ********************************************************************** --> + + + <function name="aero/elev_hinge_moment_ft_lbs"> + <description> + Elevator hinge moment in ft-lbs + HM = q * S * Cbar * ( Ch0 + Cha*alpha + Chd*delta ) + Positive causes trailing edge down movement + Ch0 is used to artifically trim HM to zero + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <value> .4492E-01</value> <!-- surface area of elevator --> + <value> .9414E-01</value> <!-- MAC of elevator --> + <sum> + <!-- + <property>aero/Ch0_elev</property> + --> + <product> + <property>aero/alpha-deg</property> + <table> <!-- Ch-alpha --> + <independentVar lookup="row"> + aero/alpha-deg</independentVar> + <tableData> + -16.00 .2169E-02 + -8.000 .2169E-02 + -6.000 .2169E-02 + -4.000 .2169E-02 + -2.000 .2169E-02 + .000 .2169E-02 + 2.000 .2169E-02 + 4.000 .2169E-02 + 8.000 .2169E-02 + 9.000 .2169E-02 + 10.00 .1730E-01 + 12.00 .1723E-01 + 14.00 .1723E-01 + 16.00 .1723E-01 + 18.00 .1723E-01 + 19.00 .1723E-01 + 20.00 .1723E-01 + 21.00 .1723E-01 + 22.00 .1724E-01 + 24.00 .1723E-01 + </tableData> + </table> + </product> + <product> + <property>fcs/elevator-pos-deg</property> + <table> <!-- Ch-delta elevator --> + <independentVar lookup="row"> + fcs/elevator-pos-deg</independentVar> + <tableData> + -20.00 .1730E-01 + -15.00 .1723E-01 + -10.00 .1723E-01 + -5.000 .1723E-01 + .000 .1723E-01 + 5.000 .1723E-01 + 10.00 .1723E-01 + 13.00 .1723E-01 + 16.00 .1724E-01 + </tableData> + </table> + </product> + </sum> + </product> + </function> + + </aerodynamics> +</fdm_config> diff --git a/aircraft/EasyStar/EasyStar-windtunnel-set.xml b/aircraft/EasyStar/EasyStar-windtunnel-set.xml new file mode 100644 index 0000000000000000000000000000000000000000..2be996c8c5338f99d3d377e5263abb5121c97475 --- /dev/null +++ b/aircraft/EasyStar/EasyStar-windtunnel-set.xml @@ -0,0 +1,20 @@ +<?xml version="1.0"?> +<PropertyList xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xsi:noNamespaceSchemaLocation="../../XMLSchemas/PropertyList.xsd"> + <sim> + <author>James Goppert</author> + <description>Multiplex Easy Star (wind tunnel)</description> + <aircraft-version>0.0.0</aircraft-version> + <status>early-production</status> + <startup> + <splash-title>Multiplex Easy Star</splash-title> + </startup> + <model> + <path>Aircraft/EasyStar/Models/EasyStar-model.xml</path> + </model> + <sound> + <path>Aircraft/EasyStar/EasyStar-sound.xml</path> + </sound> + <flight-model>jsb</flight-model> + <aero>EasyStar-windtunnel</aero> + </sim> +</PropertyList> diff --git a/aircraft/EasyStar/EasyStar-windtunnel.xml b/aircraft/EasyStar/EasyStar-windtunnel.xml new file mode 100644 index 0000000000000000000000000000000000000000..e4e281625d3d50c203b61696b2e9be394c277b6f --- /dev/null +++ b/aircraft/EasyStar/EasyStar-windtunnel.xml @@ -0,0 +1,1366 @@ +<?xml version="1.0"?> +<!-- + This is the JSBSim config file for a PA34-200T SenecaII. + The aerodynamics sections was generated by datcom using + as much real input as available. + + Changes from datcom.xml + + - function attribute NAME must be lowercase + - missing function Delta_lift_due_to_flap_deflection in axis LIFT + - missing function Lift_due_to_Elevator_Deflection in axis LIFT +--> +<?xml-stylesheet href="JSBSim.xsl" type="application/xml"?> +<fdm_config xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" + xsi:noNamespaceSchemaLocation="file:/home/torsten/FlightGear/Aircraft/SenecaII/JSBSim.xsd" + name="EasyStar-windtunnel" version="2.0" release="BETA"> + + <fileheader> + <author>James Goppert</author> + <filecreationdate>2010-6-3</filecreationdate> + <description>Multiplex Easy Star (wind tunnel)</description> + <reference title="Multiplex Easy Star (wind tunnel)"/> + </fileheader> + + <!-- ********************************************************************** + METRICS + ********************************************************************** --> + <metrics> + <wingarea unit="FT2"> 2.2792 </wingarea> + <wingspan unit="FT"> 4.5000 </wingspan> + <chord unit="FT"> .5606 </chord> + <htailarea unit="FT2"> .4457 </htailarea> + <htailarm unit="FT"> .4280 </htailarm> + <vtailarea unit="FT2"> .1606 </vtailarea> + <vtailarm unit="FT"> .7127 </vtailarm> + <!-- + the aerodynamic reference point, common point for + aerodynamic forces (lift and drag) + --> + <location name="AERORP" unit="IN"> + <x> 4.0 </x> + <y> 0.0 </y> + <z> 0.0 </z> + </location> + <!-- the eyepoint of the pilot (left or right eye?) --> + <location name="EYEPOINT" unit="IN"> + <x> 0.0 </x> + <y> 0.0 </y> + <z> 0.0 </z> + </location> + <!-- the visual reference point of the 3d model --> + <location name="VRP" unit="IN"> + <x> 0.0 </x> + <y> 0.0 </y> + <z> 0.0 </z> + </location> + </metrics> + + <!-- ********************************************************************** + MASS_BALANCE + ********************************************************************** --> + <mass_balance> + <ixx unit="SLUG*FT2"> .1 </ixx> + <iyy unit="SLUG*FT2"> .1 </iyy> + <izz unit="SLUG*FT2"> .1 </izz> + <ixz unit="SLUG*FT2"> 0 </ixz> + <emptywt unit="LBS"> 2.0 </emptywt> + <!-- the center of gravity --> + <location name="CG" unit="IN"> + <x> 3.0 </x> + <y> 0.0 </y> + <z> 0.0 </z> + </location> + <!--<pointmass name="PAYLOAD">--> + <!--<weight unit="LBS"> 0.0 </weight>--> + <!--<location name="POINTMASS" unit="IN">--> + <!--<x> 39.3 </x>--> + <!--<y> 0 </y>--> + <!--<z> 35.3 </z>--> + <!--</location>--> + <!--</pointmass>--> + </mass_balance> + <!-- ********************************************************************** + UNDERCARRIAGE + ********************************************************************** --> + <ground_reactions> + <contact type="STRUCTURE" name="TAIL_SKID"> + <location unit="IN"> + <x> 27.0 </x> + <y> 0 </y> + <z>-2.0 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + <contact type="STRUCTURE" name="NOSE"> + <location unit="IN"> + <x> -5.0 </x> + <y> 0.0 </y> + <z> 0.0 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + <contact type="STRUCTURE" name="BOTTOM_CANOPY"> + <location unit="IN"> + <x> 0.0 </x> + <y> 0.0 </y> + <z> -3.0 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + + <contact type="STRUCTURE" name="LEFT_WING"> + <location unit="IN"> + <x> -3.0 </x> + <y> -27.5 </y> + <z> 1.0 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + <contact type="STRUCTURE" name="RIGHT_WING"> + <location unit="IN"> + <x> -3.0 </x> + <y> 27.5 </y> + <z> 1.0 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + <contact type="STRUCTURE" name="VERTICAL_TAIL"> + <location unit="IN"> + <x> 27.0 </x> + <y> 0.0 </y> + <z> 6.5 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + <contact type="STRUCTURE" name="CABIN_TOP"> + <location unit="IN"> + <x> 0.0 </x> + <y> 0.0 </y> + <z> 2.0 </z> + </location> + <static_friction> 1.0 </static_friction> + <dynamic_friction> 0.8 </dynamic_friction> + <spring_coeff unit="LBS/FT"> 12 </spring_coeff> + <damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff> + </contact> + </ground_reactions> + <!-- ********************************************************************** + PROPULSION + ********************************************************************** --> + <propulsion> + <engine file="HB2815-2000"> + <location unit="IN"> + <x> 10.0 </x> + <y> 0 </y> + <z> 3.0 </z> + </location> + <orient unit="DEG"> + <roll> 0.0 </roll> + <pitch> -5 </pitch> + <yaw> 0 </yaw> + </orient> + <feed>0</feed> + <thruster file="apc6x4"> + <location unit="IN"> + <x> 10.0 </x> + <y> 0 </y> + <z> 3.0 </z> + </location> + <orient unit="DEG"> + <roll> 0.0 </roll> + <pitch> -5.0 </pitch> + <yaw> 0.0 </yaw> + </orient> + <p_factor>1.0</p_factor> + </thruster> + </engine> + <!--throws warning if tank not included, no real purpose--> + <tank type="FUEL"> <!-- Tank number 0 --> + <location unit="IN"> + <x> 0.0 </x> + <y> 0.0 </y> + <z> 0.0 </z> + </location> + <capacity unit="LBS"> 0.0001 </capacity> + <contents unit="LBS"> 0 </contents> + </tank> + </propulsion> + <!-- ********************************************************************** + FLIGHT CONTROLS + ********************************************************************** --> + <flight_control name="EasyStar"> + <!-- + Elevator + --> + <channel name="Pitch"> + <summer name="Pitch Trim Sum"> + <input>fcs/elevator-cmd-norm</input> + <input>fcs/pitch-trim-cmd-norm</input> + <clipto> + <min>-1</min> + <max>1</max> + </clipto> + <output>fcs/elevator-pos-norm</output> + </summer> + <aerosurface_scale name="Elevator Control"> + <input>fcs/pitch-trim-sum</input> + <gain>0.01745</gain> + <range> + <min>-28</min> + <max>23</max> + </range> + <output>fcs/elevator-pos-rad</output> + </aerosurface_scale> + </channel> + <!-- + Rudder + --> + <channel name="Yaw"> + <summer name="Yaw Trim Sum"> + <input>fcs/rudder-cmd-norm</input> + <input>fcs/yaw-trim-cmd-norm</input> + <clipto> + <min>-1</min> + <max>1</max> + </clipto> + </summer> + <!--<pure_gain name="Aileron Crossfeed">--> + <!--<input>fcs/aileron-cmd-norm</input>--> + <!--<gain>-1</gain>--> + <!--<output>fcs/rudder-pos-norm</output>--> + <!--</pure_gain>--> + <summer name="Yaw Mix"> + <input>fcs/yaw-trim-sum</input> + <!--<input>fcs/aileron-crossfeed</input>--> + <clipto> + <min>-1</min> + <max>1</max> + </clipto> + </summer> + <aerosurface_scale name="Rudder Control"> + <input>fcs/yaw-mix</input> + <gain>0.01745</gain> + <range> + <min>-27</min> + <max>27</max> + </range> + <output>fcs/rudder-pos-rad</output> + </aerosurface_scale> + </channel> + <!-- + Throttle (linear vs rpm approx.) + --> + <channel name="Throttle"> + <fcs_function name="fcs/rpm-scaled-throttle"> + <function> + <pow> + <property>fcs/throttle-cmd-norm</property> + <value>3</value> + </pow> + </function> + </fcs_function> + <aerosurface_scale name="Throttle Control"> + <input>fcs/rpm-scaled-throttle</input> + <range> + <min>-1</min> + <max>1</max> + </range> + <output>fcs/throttle-pos-norm</output> + </aerosurface_scale> + </channel> + + </flight_control> + +<!-- + + + ****************** IMPORTANT NOTICES ********************** + + This is an alpha version release of the DATCOM+ program for + JSBSIM. Nothing, and I do mean NOTHING, as been checked to + verify that the parameters, units, sign conventions, or + basically anything else is correct. Your mileage may vary. + + *********************************************************** + + This file was generated by the USAF Digital DATCOM program. + This file is considered an intermediary file in the + DATCOM/JSBSim process. This file may be overwritten without + warning, so any changes that you make in here may be lost. + + If you intend to use this file as it is and modify it, make + sure that you take the necessary precautions to prevent it + from being overwritten, like renaming it. + + + *********************************************************** + + + DISCLAIMER REQUIRED BY HQ USAF FOR PUBLIC RELEASE APPROVAL + + THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION + IS RELEASED "AS IS". THE U.S. GOVERNMENT MAKES NO + WARRANTY OF ANY KIND, EXPRESS OR IMPLIED, CONCERNING + THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION, + INCLUDING, WITHOUT LIMITATION, ANY WARRANTIES OF + MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE. + IN NO EVENT WILL THE U.S. GOVERNMENT BE LIABLE FOR ANY + DAMAGES, INCLUDING LOST PROFITS, LOST SAVINGS OR OTHER + INCIDENTAL OR CONSEQUENTIAL DAMAGES ARISING OUT OF THE + USE, OR INABILITY TO USE, THIS SOFTWARE OR ANY + ACCOMPANYING DOCUMENTATION, EVEN IF INFORMED IN ADVANCE + OF THE POSSIBILITY OF SUCH DAMAGES. + + + *********************************************************** +--> + + + + + + + +<!-- ********************************************************************** + AERODYNAMICS + ********************************************************************** +--> + + + <aerodynamics> + + <alphalimits unit="DEG"> + <min> -16.00 </min> + <max> 24.00 </max> + </alphalimits> + + + + + <!-- ************************* + Sign Conventions + ************************* + + Control displacements + Stick FWD + / Aft - + Stick Left + / Right - + Wheel CCW + / CW - + Pedal Left + / Right - + Elevator trim Nose Up + / Nose down - + + Surfaces + Elevator TED + / TEU - + R Ail TED + / TEU - + L Ail TED + / TEU - + Rudder TEL + / TER - + + F&M, Accel, Rates, Displacements + Pitch Up + / Down - + Roll Rgt + / Left - + Yaw Rgt + / Left - + + Other + Alpha Up + / Down - + Beta Wind in right ear + / Wind in left ear - + Slip Ball right of center + / left of center - + --> + + + + + <!-- ************************************** + ASSUMPTIONS AND LIMITATIONS + + There is no interaction between deflected surfaces modeled + so there is no change in elevator effects with the flaps + deflected, for example. + + Terms known to be missing from DATCOM: + Power effects + Ground effects + Cyr, CyDr, Cyda, ClDr, Cndr + + ************************************** + --> + + + <!-- + The following ground effect tables are NOT generated + by DATCOM, but provide representative effects. + These terms are not currently used in this model. + --> + + + <function name="aero/function/ground-effect-factor-lift"> + <description>Change in lift due to ground effect factor</description> + <product> + <table> + <independentVar lookup="row">aero/h_b-mac-ft</independentVar> + <tableData> + 0.0 1.203 + 0.1 1.127 + 0.15 1.090 + 0.2 1.073 + 0.3 1.046 + 0.4 1.055 + 0.5 1.019 + 0.6 1.013 + 0.7 1.008 + 0.8 1.006 + 0.9 1.003 + 1.0 1.002 + 1.1 1.0 + </tableData> + </table> + </product> + </function> + + <function name="aero/function/ground-effect-factor-drag"> + <description>Change in drag due to ground effect</description> + <product> + <table> + <independentVar lookup="row">aero/h_b-mac-ft</independentVar> + <tableData> + 0.0 0.480 + 0.1 0.515 + 0.15 0.629 + 0.2 0.709 + 0.3 0.815 + 0.4 0.882 + 0.5 0.928 + 0.6 0.962 + 0.7 0.988 + 0.8 1.0 + 0.9 1.0 + 1.0 1.0 + 1.1 1.0 + </tableData> + </table> + </product> + </function> + + + + + +<!-- ********************************************************************** --> + + + <axis name="LIFT"> + + + <function name="aero/coefficient/CLwbh"> + <description> + Lift due to alpha + Increase in CL decreases Period and damping,Dutch Roll damping + CL is low for landing + </description> + <product> + <property>aero/function/ground-effect-factor-lift</property> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -8.00 -0.06335 + -6.00 0.038907 + -4.00 0.206593 + -2.00 0.345895 + 0.00 0.457604 + 2.00 0.590396 + 4.00 0.716654 + 6.00 0.881424 + 8.00 0.979728 + 10.00 1.086794 + 11.00 1.132822 + 12.00 1.181349 + 13.00 1.193517 + 14.00 1.204571 + 15.00 1.21972 + 16.00 1.216158 + 17.00 1.155675 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/CLq"> + <description> + Basic Lift Coefficient due to pitch rate(per degree) + </description> + <product> + <property>velocities/q-aero-rad_sec</property> + <value>57.29577951</value> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>aero/ci2vel</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 .1523 + -8.000 .1523 + -6.000 .1523 + -4.000 .1523 + -2.000 .1523 + .000 .1523 + 2.000 .1523 + 4.000 .1523 + 8.000 .1523 + 9.000 .1523 + 10.00 .1523 + 12.00 .1523 + 14.00 .1523 + 16.00 .1523 + 18.00 .1523 + 19.00 .1523 + 20.00 .1523 + 21.00 .1523 + 22.00 .1523 + 24.00 .1523 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/CLad"> + <description> + Basic Lift Coefficient due to AOA rate(per degree) + Important contributor to Short-Period damping + For low Cla, aircraft must land at high alpha + </description> + <product> + <property>aero/alphadot-deg_sec</property> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>aero/ci2vel</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + <!---16.00 .3510E-01--> + <!---8.000 .3144E-01--> + <!---6.000 .3313E-01--> + <!---4.000 .3315E-01--> + <!---2.000 .3284E-01--> + <!--.000 .3296E-01--> + <!--2.000 .3277E-01--> + <!--4.000 .3230E-01--> + <!--8.000 .2898E-01--> + <!--9.000 .2806E-01--> + <!--10.00 .2572E-01--> + <!--12.00 .1946E-01--> + <!--14.00 .1550E-01--> + <!--16.00 .1016E-01--> + <!--18.00 -.2053E-02--> + <!--19.00 -.1167E-01--> + <!--20.00 -.3353E-01--> + <!--21.00 -.5670E-01--> + <!--22.00 -.5279E-01--> + <!--24.00 -.3183E-01--> + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/CLDe"> + <description> + Lift Coefficient due to Elevator Deflection + Positive surface deflection is trailing edge down + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <table> + <independentVar lookup="row">fcs/elevator-pos-deg</independentVar> + <tableData> + -20.00 -.6476E-01 + -15.00 -.5856E-01 + -10.00 -.4002E-01 + -5.000 -.2001E-01 + .000 .4002E-04 + 5.000 .2001E-01 + 10.00 .4002E-01 + 13.00 .5157E-01 + 16.00 .6162E-01 + </tableData> + </table> + </product> + </function> + + </axis> + + + + +<!-- ********************************************************************** --> + + + <axis name="DRAG"> + + + <function name="aero/coefficient/CD"> + <description> + Basic Drag Coefficient + Sense: Always positive + Main contributor to Phugoid damping: Greater Cd, Better damping + </description> + <product> + <property>aero/function/ground-effect-factor-lift</property> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -8.00 0.054935 + -6.00 0.054319 + -4.00 0.049043 + -2.00 0.054276 + 0.00 0.058332 + 2.00 0.053311 + 4.00 0.058928 + 6.00 0.068195 + 8.00 0.083696 + 10.00 0.090816 + 11.00 0.105498 + 12.00 0.123163 + 13.00 0.125782 + 14.00 0.141154 + 15.00 0.147641 + 16.00 0.174355 + 17.00 0.207037 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/CdDe"> + <description> + Drag Coefficient due to Elevator Deflection + Positive surface deflection is trailing edge down + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <independentVar lookup="column">fcs/elevator-pos-deg</independentVar> + <tableData> + -20.00 -15.00 -10.00 -5.000 .000 5.000 10.00 13.00 16.00 + -16.00 .5945E-02 .5210E-02 .3237E-02 .1444E-02 -.2539E-05 -.1095E-02 -.1842E-02 -.2114E-02 -.2256E-02 + -8.000 .3346E-02 .2862E-02 .1633E-02 .6419E-03 -.9344E-06 -.2931E-03 -.2373E-03 -.4624E-04 .2148E-03 + -6.000 .2700E-02 .2278E-02 .1234E-02 .4425E-03 -.5355E-06 -.9363E-04 .1616E-03 .4677E-03 .8290E-03 + -4.000 .2027E-02 .1671E-02 .8186E-03 .2349E-03 -.1202E-06 .1140E-03 .5768E-03 .1003E-02 .1468E-02 + -2.000 .1338E-02 .1048E-02 .3930E-03 .2209E-04 .3054E-06 .3268E-03 .1002E-02 .1551E-02 .2124E-02 + .000 .6550E-03 .4315E-03 -.2832E-04 -.1886E-03 .7268E-06 .5375E-03 .1424E-02 .2094E-02 .2773E-02 + 2.000 -.3080E-04 -.1879E-03 -.4516E-03 -.4002E-03 .1150E-05 .7491E-03 .1847E-02 .2640E-02 .3425E-02 + 4.000 -.7194E-03 -.8099E-03 -.8767E-03 -.6128E-03 .1575E-05 .9616E-03 .2272E-02 .3187E-02 .4079E-02 + 8.000 -.2133E-02 -.2087E-02 -.1749E-02 -.1049E-02 .2448E-05 .1398E-02 .3145E-02 .4312E-02 .5423E-02 + 9.000 -.2513E-02 -.2429E-02 -.1984E-02 -.1166E-02 .2683E-05 .1515E-02 .3379E-02 .4614E-02 .5784E-02 + 10.00 -.2896E-02 -.2776E-02 -.2220E-02 -.1285E-02 .2920E-05 .1633E-02 .3616E-02 .4919E-02 .6148E-02 + 12.00 -.3763E-02 -.3559E-02 -.2755E-02 -.1552E-02 .3453E-05 .1901E-02 .4151E-02 .5608E-02 .6972E-02 + 14.00 -.4698E-02 -.4403E-02 -.3333E-02 -.1841E-02 .4031E-05 .2190E-02 .4728E-02 .6352E-02 .7861E-02 + 16.00 -.5692E-02 -.5301E-02 -.3946E-02 -.2148E-02 .4650E-05 .2496E-02 .5342E-02 .7143E-02 .8806E-02 + 18.00 -.6799E-02 -.6301E-02 -.4629E-02 -.2489E-02 .5328E-05 .2838E-02 .6025E-02 .8023E-02 .9858E-02 + 19.00 -.7457E-02 -.6895E-02 -.5036E-02 -.2692E-02 .5729E-05 .3041E-02 .6431E-02 .8547E-02 .1048E-01 + 20.00 -.8200E-02 -.7566E-02 -.5494E-02 -.2921E-02 .6195E-05 .3270E-02 .6889E-02 .9137E-02 .1119E-01 + 21.00 -.9209E-02 -.8478E-02 -.6117E-02 -.3233E-02 .6812E-05 .3582E-02 .7512E-02 .9940E-02 .1215E-01 + 22.00 -.1032E-01 -.9484E-02 -.6805E-02 -.3577E-02 .7499E-05 .3926E-02 .8201E-02 .1083E-01 .1321E-01 + 24.00 -.1205E-01 -.1104E-01 -.7870E-02 -.4109E-02 .8561E-05 .4458E-02 .9265E-02 .1220E-01 .1485E-01 + </tableData> + </table> + </product> + </function> + + </axis> + + + + +<!-- ********************************************************************** --> + + + <axis name="SIDE"> + + + <function name="aero/coefficient/Cyb"> + <description> + Side Force coefficient due to Sideslip(per degree) + Contributes to damping of Dutch Roll mode + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>aero/beta-deg</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.3898E-02 + -8.000 -.3898E-02 + -6.000 -.3898E-02 + -4.000 -.3898E-02 + -2.000 -.3898E-02 + .000 -.3898E-02 + 2.000 -.3898E-02 + 4.000 -.3898E-02 + 8.000 -.3898E-02 + 9.000 -.3898E-02 + 10.00 -.3898E-02 + 12.00 -.3898E-02 + 14.00 -.3898E-02 + 16.00 -.3898E-02 + 18.00 -.3898E-02 + 19.00 -.3898E-02 + 20.00 -.3898E-02 + 21.00 -.3898E-02 + 22.00 -.3898E-02 + 24.00 -.3898E-02 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/Cyp"> + <description> + Side Force Coefficient due to Roll Rate(per degree) + </description> + <product> + <property>velocities/p-aero-rad_sec</property> + <value>57.29577951</value> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>aero/bi2vel</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.6446E-03 + -8.000 -.1072E-02 + -6.000 -.1171E-02 + -4.000 -.1268E-02 + -2.000 -.1364E-02 + .000 -.1460E-02 + 2.000 -.1555E-02 + 4.000 -.1651E-02 + 8.000 -.1855E-02 + 9.000 -.1955E-02 + 10.00 -.2099E-02 + 12.00 -.2372E-02 + 14.00 -.2653E-02 + 16.00 -.3034E-02 + 18.00 -.3638E-02 + 19.00 -.1454E-01 + 20.00 -.5140E-03 + 21.00 -.1285E-02 + 22.00 -.1322E-02 + 24.00 -.1076E-02 + </tableData> + </table> + </product> + </function> + + + <!-- ************************* + Not calculated by DATCOM+ + ************************* + --> + + <function name="aero/coefficient/Cyr"> + <description> + Side Force due to Yaw Rate(DATCOM does not calculate) + Effect is small + </description> + <product> + <property>velocities/r-aero-rad_sec</property> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>aero/bi2vel</property> + <value> .000 </value> + </product> + </function> + + + <!-- ************************* + Not calculated by DATCOM+ + ************************* + --> + + <function name="aero/coefficient/CyDr"> + <description> + Side Force due to rudder(DATCOM does not calculate) + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>fcs/rudder-pos-deg</property> + <value> .000 </value> + </product> + </function> + + + <!-- ************************* + Not calculated by DATCOM+ + ************************* + --> + + <function name="aero/coefficient/CyDa"> + <description> + Side Force due to aileron(DATCOM does not calculate) + Usually neglected + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>fcs/left-aileron-pos-deg</property> + <value> .000 </value> + </product> + </function> + + </axis> + + + + +<!-- ********************************************************************** --> + + + <axis name="ROLL"> + + + <function name="aero/coefficient/Clb"> + <description> + Roll Moment coefficient due to Beta(per degree) + Decrease of Clb to small negative value improves Dutch Roll Damping + High Positive value leads to excessive spiral instability + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>aero/beta-deg</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.1224E-02 + -8.000 -.1221E-02 + -6.000 -.1219E-02 + -4.000 -.1216E-02 + -2.000 -.1212E-02 + .000 -.1208E-02 + 2.000 -.1206E-02 + 4.000 -.1204E-02 + 8.000 -.1203E-02 + 9.000 -.1204E-02 + 10.00 -.1202E-02 + 12.00 -.1194E-02 + 14.00 -.1181E-02 + 16.00 -.1162E-02 + 18.00 -.1134E-02 + 19.00 -.1116E-02 + 20.00 -.1082E-02 + 21.00 -.1034E-02 + 22.00 -.9825E-03 + 24.00 -.9008E-03 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/Clp"> + <description> + Roll Moment coefficient due to roll rate(per degree) + Clp alone determines damping-in-roll characteristics + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>aero/bi2vel</property> + <property>velocities/p-aero-rad_sec</property> + <!--Manually increased roll damping, problem with datcom?--> + <value>-0.5</value> + <!--<table>--> + <!--<independentVar lookup="row">aero/alpha-deg</independentVar>--> + <!--<tableData>--> + <!---16.00 -.7650E-02--> + <!---8.000 -.7063E-02--> + <!---6.000 -.6859E-02--> + <!---4.000 -.6653E-02--> + <!---2.000 -.6738E-02--> + <!--.000 -.7039E-02--> + <!--2.000 -.7303E-02--> + <!--4.000 -.7498E-02--> + <!--8.000 -.7737E-02--> + <!--9.000 -.7239E-02--> + <!--10.00 -.6298E-02--> + <!--12.00 -.4816E-02--> + <!--14.00 -.3420E-02--> + <!--16.00 -.1548E-02--> + <!--18.00 .8581E-03--> + <!--19.00 .5957E-02--> + <!--20.00 .1465E-01--> + <!--21.00 .1964E-01--> + <!--22.00 .1776E-01--> + <!--24.00 .7247E-02--> + <!--</tableData>--> + <!--</table>--> + </product> + </function> + + <function name="aero/coefficient/Clr"> + <description> + Roll Moment coefficient due to yaw rate(per degree) + Considerable effect on Spiral mode. Large + positive values leads to strong sprial instability. + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>aero/bi2vel</property> + <property>velocities/r-aero-rad_sec</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.3497E-02 + -8.000 -.1073E-02 + -6.000 -.4976E-03 + -4.000 .5472E-04 + -2.000 .5948E-03 + .000 .1162E-02 + 2.000 .1754E-02 + 4.000 .2366E-02 + 8.000 .3626E-02 + 9.000 .3944E-02 + 10.00 .4217E-02 + 12.00 .4651E-02 + 14.00 .4975E-02 + 16.00 .5166E-02 + 18.00 .5164E-02 + 19.00 .5079E-02 + 20.00 .4606E-02 + 21.00 .3766E-02 + 22.00 .2861E-02 + 24.00 .1748E-02 + </tableData> + </table> + </product> + </function> + + + <!-- ************************* + Not calculated by DATCOM+ + ************************* + --> + + <function name="aero/coefficient/ClDr"> + <description> + Roll moment due to rudder(DATCOM does not calculate) + Usually insignificant in dynamic stability considerations + but is used in autopilot work + </description> + <product> + <property>metrics/bw-ft</property> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>fcs/rudder-pos-deg</property> + <value> .000 </value> + </product> + </function> + + </axis> + + + + +<!-- ********************************************************************** --> + + + <axis name="PITCH"> + + + <function name="aero/coefficient/Cm_basic"> + <description> + Basic_Pitch_moment_coefficient + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/cbarw-ft</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 .6261 + -8.000 .2937 + -6.000 .2325 + -4.000 .1590 + -2.000 .7771E-01 + .000 -.5162E-02 + 2.000 -.9019E-01 + 4.000 -.1784 + 8.000 -.3681 + 9.000 -.4190 + 10.00 -.4685 + 12.00 -.5701 + 14.00 -.6714 + 16.00 -.7712 + 18.00 .000 + 19.00 .000 + 20.00 .000 + 21.00 .000 + 22.00 .000 + 24.00 .000 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/Cmq"> + <description> + Pitch moment coefficient due to pitch rate(per degree) + Pitch Damping Derivative + Very important to Short Period damping of oscillations + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/cbarw-ft</property> + <property>aero/ci2vel</property> + <property>velocities/q-aero-rad_sec</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.2485 + -8.000 -.2485 + -6.000 -.2485 + -4.000 -.2485 + -2.000 -.2485 + .000 -.2485 + 2.000 -.2485 + 4.000 -.2485 + 8.000 -.2485 + 9.000 -.2485 + 10.00 -.2485 + 12.00 -.2485 + 14.00 -.2485 + 16.00 -.2485 + 18.00 -.2485 + 19.00 -.2485 + 20.00 -.2485 + 21.00 -.2485 + 22.00 -.2485 + 24.00 -.2485 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/Cmadot"> + <description> + Pitch moment coefficient due to AOA rate(per degree) + Negitive Cmad increase Short Period damping + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/cbarw-ft</property> + <property>aero/ci2vel</property> + <property>aero/alphadot-deg_sec</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.1061 + -8.000 -.9502E-01 + -6.000 -.1001 + -4.000 -.1002 + -2.000 -.9926E-01 + .000 -.9960E-01 + 2.000 -.9904E-01 + 4.000 -.9762E-01 + 8.000 -.8757E-01 + 9.000 -.8480E-01 + 10.00 -.7772E-01 + 12.00 -.5882E-01 + 14.00 -.4683E-01 + 16.00 -.3071E-01 + 18.00 .6206E-02 + 19.00 .3526E-01 + 20.00 .1013 + 21.00 .1714 + 22.00 .1595 + 24.00 .9619E-01 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/CmDe"> + <description> + Pitch moment coefficient due to elevator deflection + Positive surface deflection is trailing edge down + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/cbarw-ft</property> + <table> + <independentVar lookup="row">fcs/elevator-pos-deg</independentVar> + <tableData> + -20.00 .2086 + -15.00 .1871 + -10.00 .1282 + -5.000 .6409E-01 + .000 -.1282E-03 + 5.000 -.6409E-01 + 10.00 -.1282 + 13.00 -.1648 + 16.00 -.1970 + </tableData> + </table> + </product> + </function> + + </axis> + + + + +<!-- ********************************************************************** --> + + + <axis name="YAW"> + + + <function name="aero/coefficient/Cnb"> + <description> + Yaw moment coefficient due to sideslip(per degree) + Determines Dutch Roll and Spiral characteristics + Prevents side-slip and yawing moments + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>aero/beta-deg</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 .6403E-03 + -8.000 .6403E-03 + -6.000 .6403E-03 + -4.000 .6403E-03 + -2.000 .6403E-03 + .000 .6403E-03 + 2.000 .6403E-03 + 4.000 .6403E-03 + 8.000 .6403E-03 + 9.000 .6403E-03 + 10.00 .6403E-03 + 12.00 .6403E-03 + 14.00 .6403E-03 + 16.00 .6403E-03 + 18.00 .6403E-03 + 19.00 .6403E-03 + 20.00 .6403E-03 + 21.00 .6403E-03 + 22.00 .6403E-03 + 24.00 .6403E-03 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/Cnp"> + <description> + Yaw moment coefficient due to roll rate(per degree) + Reduces Dutch Roll damping + positive value desireable + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>aero/bi2vel</property> + <property>velocities/p-aero-rad_sec</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 .2909E-03 + -8.000 .1580E-03 + -6.000 .1150E-03 + -4.000 .5960E-04 + -2.000 .8267E-06 + .000 -.4457E-04 + 2.000 -.7403E-04 + 4.000 -.9603E-04 + 8.000 -.1448E-03 + 9.000 -.2952E-03 + 10.00 -.5744E-03 + 12.00 -.1081E-02 + 14.00 -.1590E-02 + 16.00 -.2209E-02 + 18.00 -.2839E-02 + 19.00 -.1963E-02 + 20.00 -.6663E-02 + 21.00 -.6409E-02 + 22.00 -.4810E-02 + 24.00 -.2047E-02 + </tableData> + </table> + </product> + </function> + + <function name="aero/coefficient/Cnr"> + <description> + Yaw Moment coefficient due to yaw rate(per degree) + Main contributor to damping of Dutch Roll + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>aero/bi2vel</property> + <property>velocities/r-aero-rad_sec</property> + <table> + <independentVar lookup="row">aero/alpha-deg</independentVar> + <tableData> + -16.00 -.8275E-03 + -8.000 -.7745E-03 + -6.000 -.7758E-03 + -4.000 -.7821E-03 + -2.000 -.7927E-03 + .000 -.8079E-03 + 2.000 -.8285E-03 + 4.000 -.8551E-03 + 8.000 -.9275E-03 + 9.000 -.9496E-03 + 10.00 -.9698E-03 + 12.00 -.1004E-02 + 14.00 -.1030E-02 + 16.00 -.1043E-02 + 18.00 -.1037E-02 + 19.00 -.1026E-02 + 20.00 -.9793E-03 + 21.00 -.9093E-03 + 22.00 -.8479E-03 + 24.00 -.7868E-03 + </tableData> + </table> + </product> + </function> + + + <!-- ****************************************************** + CnDr is not calculated by DATCOM+, but a default value + is supplied + ******************************************************--> + + <function name="aero/coefficient/CnDr"> + <description> + Yaw Coefficient due to rudder(DATCOM does not calculate) + High value for controllablity, low value + for good dynamic stability + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <property>metrics/bw-ft</property> + <property>fcs/rudder-pos-deg</property> + <value> -.1047E-02</value> + </product> + </function> + + + </axis> + + + + +<!-- ********************************************************************** --> + + + <function name="aero/elev_hinge_moment_ft_lbs"> + <description> + Elevator hinge moment in ft-lbs + HM = q * S * Cbar * ( Ch0 + Cha*alpha + Chd*delta ) + Positive causes trailing edge down movement + Ch0 is used to artifically trim HM to zero + </description> + <product> + <property>aero/qbar-psf</property> + <property>metrics/Sw-sqft</property> + <value> .4492E-01</value> <!-- surface area of elevator --> + <value> .9414E-01</value> <!-- MAC of elevator --> + <sum> + <!-- + <property>aero/Ch0_elev</property> + --> + <product> + <property>aero/alpha-deg</property> + <table> <!-- Ch-alpha --> + <independentVar lookup="row"> + aero/alpha-deg</independentVar> + <tableData> + -16.00 .2169E-02 + -8.000 .2169E-02 + -6.000 .2169E-02 + -4.000 .2169E-02 + -2.000 .2169E-02 + .000 .2169E-02 + 2.000 .2169E-02 + 4.000 .2169E-02 + 8.000 .2169E-02 + 9.000 .2169E-02 + 10.00 .1730E-01 + 12.00 .1723E-01 + 14.00 .1723E-01 + 16.00 .1723E-01 + 18.00 .1723E-01 + 19.00 .1723E-01 + 20.00 .1723E-01 + 21.00 .1723E-01 + 22.00 .1724E-01 + 24.00 .1723E-01 + </tableData> + </table> + </product> + <product> + <property>fcs/elevator-pos-deg</property> + <table> <!-- Ch-delta elevator --> + <independentVar lookup="row"> + fcs/elevator-pos-deg</independentVar> + <tableData> + -20.00 .1730E-01 + -15.00 .1723E-01 + -10.00 .1723E-01 + -5.000 .1723E-01 + .000 .1723E-01 + 5.000 .1723E-01 + 10.00 .1723E-01 + 13.00 .1723E-01 + 16.00 .1724E-01 + </tableData> + </table> + </product> + </sum> + </product> + </function> + + </aerodynamics> +</fdm_config> diff --git a/scicoslab/scripts/fgrun.sh b/scicoslab/scripts/fgrun.sh index 992d8c0cfeae5a8cce38054b1388c8ce15e084b8..3f77e5f69aa3250d48be285126623a2c13d76f74 100755 --- a/scicoslab/scripts/fgrun.sh +++ b/scicoslab/scripts/fgrun.sh @@ -1,11 +1,14 @@ #!/bin/bash -#--native-ctrls=socket,out,119,,5501,udp \ -#--native-ctrls=socket,in,120,,5502,udp \ +#--disable-textures \ +if [ $# != 1 ] +then + echo usage: $0 aircraft + exit +fi +aircraft=$1 fgfs \ ---fdm=external \ ---aircraft=c172p \ +--aircraft=$aircraft \ --geometry=400x300 \ ---native-fdm=socket,in,120,,5500,udp \ --vc=30 \ --altitude=1000 \ --heading=90 \ @@ -17,7 +20,6 @@ fgfs \ --shading-flat \ --notrim \ --fog-disable \ ---disable-textures \ --disable-specular-highlight \ --disable-skyblend \ --disable-random-objects \ diff --git a/scicoslab/scripts/fgrunExt.sh b/scicoslab/scripts/fgrunExt.sh new file mode 100755 index 0000000000000000000000000000000000000000..ed9bd8012acf9ff87ab04f83484b411fef26ee3b --- /dev/null +++ b/scicoslab/scripts/fgrunExt.sh @@ -0,0 +1,33 @@ +#!/bin/bash +#--native-ctrls=socket,out,119,,5501,udp \ +#--native-ctrls=socket,in,120,,5502,udp \ +#--disable-textures \ +if [ $# != 1 ] +then + echo usage: $0 aircraft + exit +fi +aircraft=$1 +fgfs \ +--fdm=external \ +--aircraft=$aircraft \ +--geometry=400x300 \ +--native-fdm=socket,in,120,,5500,udp \ +--vc=30 \ +--altitude=1000 \ +--heading=90 \ +--roll=0 \ +--pitch=0 \ +--wind=0@0 \ +--turbulence=0.0 \ +--timeofday=noon \ +--shading-flat \ +--notrim \ +--fog-disable \ +--disable-specular-highlight \ +--disable-skyblend \ +--disable-random-objects \ +--disable-panel \ +--disable-horizon-effect \ +--disable-clouds \ +--disable-anti-alias-hud