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A380-aero.xml
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A380-aero.xml
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<?xml version="1.0"?><!-- minor changes by ph-cor jan2016 -->
<aerodynamics>
<axis name="DRAG">
<function name="aero/coefficient/CD0">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-1.5700 1.6000
-0.2600 0.0360
0.0000 0.0180
0.2600 0.0360
1.5700 1.6000
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDi">
<description>Induced_drag</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/cl-squared</property>
<value>0.0350</value>
</product>
</function>
<function name="aero/coefficient/CDmach">
<description>Drag_due_to_mach</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 0.0000
0.7900 0.0000
1.1000 0.0230
1.8000 0.0150
</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>
<table>
<independentVar>fcs/flap-pos-norm</independentVar>
<tableData>
0.00 0.00 <!-- 0.00 -->
0.25 0.010 <!-- 0.010 -->
0.53 0.025 <!-- 0.025 -->
0.79 0.040 <!-- 0.040 -->
1.00 0.075 <!-- 0.075 -->
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDslat">
<description>Drag_due_to_slats</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/slat-cmd-norm</property>
<value>0.012</value>
</product>
</function>
<function name="aero/coefficient/CDgear">
<description>Drag_due_to_gear</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>gear/unit[2]/pos-norm</property><!-- FIXME -->
<value>0.0110</value><!-- 0.0110 -->
</product>
</function>
<!-- To reduce the number of functions requires, I've combined the spoilers that work together - this is determined by the functions and hydraulic systems they're connected to -->
<!-- GROUP A - Spoilers that are not used for roll control and are running only on the YELLOW hydraulic system - LSP1, LSP3, RSP1 and RSP3 -->
<function name="aero/coefficient/CDsb_gr_a">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/lsp1-fbw-output</property> <!-- normalized value -->
<value>0.01</value>
</product>
</function>
<!-- GROUP B - Spoilers that are not used for roll control and are running only on the GREEN hydraulic system - LSP2, LSP4, RSP2 and RSP4 -->
<function name="aero/coefficient/CDsb_gr_b">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/lsp2-fbw-output</property> <!-- normalized value -->
<value>0.01</value>
</product>
</function>
<!-- GROUP C - Spoilers that are not used for roll control and run on either the YELLOW or ELEC hydraulic backup system - LSP5 and RSP5 -->
<function name="aero/coefficient/CDsb_gr_c">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/lsp5-fbw-output</property> <!-- normalized value -->
<value>0.006</value>
</product>
</function>
<!-- GROUP D - Spoilers that are not used for roll control and run on either the GREEN or ELEC hydraulic backup system - LSP6 and RSP6 -->
<function name="aero/coefficient/CDsb_gr_d">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/lsp6-fbw-output</property> <!-- normalized value -->
<value>0.006</value>
</product>
</function>
<!-- The below spoilers are also used for roll control, so the output positions may be different -->
<!-- LSP8 -->
<function name="aero/coefficient/CDsb_lsp8">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/lsp8-fbw-output</property> <!-- normalized value -->
<value>0.008</value>
</product>
</function>
<!-- LSP7 -->
<function name="aero/coefficient/CDsb_lsp7">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/lsp7-fbw-output</property> <!-- normalized value -->
<value>0.007</value>
</product>
</function>
<!-- RSP7 -->
<function name="aero/coefficient/CDsb_rsp7">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rsp7-fbw-output</property> <!-- normalized value -->
<value>0.007</value>
</product>
</function>
<!-- RSP8 -->
<function name="aero/coefficient/CDsb_rsp8">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rsp8-fbw-output</property> <!-- normalized value -->
<value>0.008</value>
</product>
</function>
<!-- For the ailerons, the drag due to left and right ailerons are summed -->
<!-- Outboard Ailerons -->
<function name="aero/coefficient/CDalrn_ob">
<description>Drag_due_to_ailerons</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/alrn-lob-fbw-output-abs</property> <!-- absolute normalized value -->
<value>0.0008</value>
</product>
</function>
<!-- Middle Ailerons -->
<function name="aero/coefficient/CDalrn_mid">
<description>Drag_due_to_ailerons</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/alrn-lmd-fbw-output-abs</property> <!-- absolute normalized value -->
<value>0.00064</value>
</product>
</function>
<!-- Inboard Ailerons -->
<function name="aero/coefficient/CDalrn_ib">
<description>Drag_due_to_ailerons</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/alrn-lib-fbw-output-abs</property> <!-- absolute normalized value -->
<value>0.00064</value>
</product>
</function>
<function name="aero/coefficient/CDbeta">
<description>Drag_due_to_sideslip</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>aero/beta-rad</independentVar>
<tableData>
-1.5700 1.2300
-0.2600 0.0500
0.0000 0.0000
0.2600 0.0500
1.5700 1.2300
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDde">
<description>Drag_due_to_Elevator_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-norm</property>
<value>0.0550</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>
<value>-1.0000</value>
</product>
</function>
</axis>
<!-- FIXME - I have an XFLR5 analysis going on the A380, but it doesn't seem to be letting me do a viscous test. Invscid test results are alright up to a certain point but it does not reduce the lift co-efficient as you hit the stall/critical AoA, so I haven't used those values in here. ~Naru -->
<axis name="LIFT">
<function name="aero/coefficient/CLalpha">
<description>Lift_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData><!-- lower values to achieve speedvector circle more in line with the line of sight circle at full speed -->
-0.2000 -0.6800 <!-- -0.6800 -->
0.0000 0.3500 <!-- 0.4500 -->
0.0400 0.8500 <!-- 0.9500 -->
0.2300 1.3000 <!-- 1.4500 -->
0.6000 0.7000 <!-- 0.7400 -->
</tableData>
</table>
</product>
</function>
<!-- orig property>fcs/flap-pos-norm</property -->
<!-- orig value>1.5000</value -->
<function name="aero/coefficient/dCLflap">
<description>Delta_Lift_due_to_flaps</description> <!-- adapted to achieve flaps1 190, flaps2 170, flaps3 155, flaps4 140 kts at startup fuel and load , data were 0.000 0.16 0.29 0.35 and 0.52-->
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>fcs/flap-pos-deg</independentVar>
<tableData>
00.00 0.000 <!-- 000 -->
07.23 0.180 <!-- 160 -->
15.46 0.410 <!-- 290 -->
23.64 0.660 <!-- 350 -->
30.00 0.890 <!-- 520 -->
</tableData>
</table>
</product>
</function>
<!-- Spoiler Groups are managed similar to the drag axis -->
<function name="aero/coefficient/dCLsb_gr_a">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/lsp1-fbw-output</property>
<value>-0.032</value>
</product>
</function>
<function name="aero/coefficient/dCLsb_gr_b">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/lsp2-fbw-output</property>
<value>-0.032</value>
</product>
</function>
<function name="aero/coefficient/dCLsb_gr_c">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/lsp5-fbw-output</property>
<value>-0.016</value>
</product>
</function>
<function name="aero/coefficient/dCLsb_gr_d">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/lsp6-fbw-output</property>
<value>-0.016</value>
</product>
</function>
<!-- Individual (roll control) spoilers -->
<function name="aero/coefficient/dCLsb_lsp7">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/lsp7-fbw-output</property>
<value>-0.008</value>
</product>
</function>
<function name="aero/coefficient/dCLsb_lsp8">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/lsp8-fbw-output</property>
<value>-0.012</value>
</product>
</function>
<function name="aero/coefficient/dCLsb_rsp7">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rsp7-fbw-output</property>
<value>-0.008</value>
</product>
</function>
<function name="aero/coefficient/dCLsb_rsp8">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rsp8-fbw-output</property>
<value>-0.012</value>
</product>
</function>
<function name="aero/coefficient/CLde">
<description>Lift_due_to_Elevator_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-rad</property>
<value>0.025</value><!-- 0.2000 halved three times for preciser pitch steering -->
</product>
</function>
<function name="aero/coefficient/CLdalnr_ob_droop">
<description>Lift_due_to_Aileron_Droop</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/alrn-ob-droop</property>
<value>0.0035</value>
</product>
</function>
<function name="aero/coefficient/CLdalnr_md_droop">
<description>Lift_due_to_Aileron_Droop</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/alrn-md-droop</property>
<value>0.002</value>
</product>
</function>
<function name="aero/coefficient/CLdalnr_ib_droop">
<description>Lift_due_to_Aileron_Droop</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/alrn-ib-droop</property>
<value>0.002</value>
</product>
</function>
</axis>
<axis name="ROLL">
<function name="aero/coefficient/Clb">
<description>Roll_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<value>-0.2000</value><!-- -1000 -->
</product>
</function>
<function name="aero/coefficient/Clp">
<description>Roll_moment_due_to_roll_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<value>-0.8000</value><!-- -0.4000 -->
</product>
</function>
<function name="aero/coefficient/Clr">
<description>Roll_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value>0.1000</value><!-- 0.1500 -->
</product>
</function>
<!-- Outboard Ailerons Differential Roll -->
<function name="aero/coefficient/Clda_ob">
<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/alrn-ob-diff-norm</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 0.0200
2.0000 0.0150
</tableData>
</table>
</product>
</function>
<!-- Middle Ailerons Differential Roll -->
<function name="aero/coefficient/Clda_md">
<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/alrn-md-diff-norm</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 0.0150
2.0000 0.0100
</tableData>
</table>
</product>
</function>
<!-- Inboard Ailerons Differential Roll -->
<function name="aero/coefficient/Clda_ib">
<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/alrn-ib-diff-norm</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 0.0140
2.0000 0.0070
</tableData>
</table>
</product>
</function>
<!-- Left Spoiler 8 Roll Effect -->
<function name="aero/coefficient/Cld_lsp8">
<description>Roll_moment_due_to_Spoilers</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/lsp8-fbw-output</property>
<value>-0.0040</value>
</product>
</function>
<!-- Left Spoiler 7 Roll Effect -->
<function name="aero/coefficient/Cld_lsp7">
<description>Roll_moment_due_to_Spoilers</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/lsp7-fbw-output</property>
<value>-0.0030</value>
</product>
</function>
<!-- Right Spoiler 8 Roll Effect -->
<function name="aero/coefficient/Cld_rsp8">
<description>Roll_moment_due_to_Spoilers</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rsp8-fbw-output</property>
<value>0.0040</value>
</product>
</function>
<!-- Right Spoiler 7 Roll Effect -->
<function name="aero/coefficient/Cld_rsp7">
<description>Roll_moment_due_to_Spoilers</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rsp7-fbw-output</property>
<value>0.0030</value>
</product>
</function>
<function name="aero/coefficient/Cldr">
<description>Roll_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value>0.0100</value>
</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>
<value>-0.1750</value><!-- -0.7000 2 times halved for preciser pitch under a/p -->
</product>
</function>
<function name="aero/coefficient/Cmde_hstab">
<description>Pitch_moment_due_to_hstab</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/hstab-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 -0.8000
2.0000 -0.3250
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmde_lob">
<description>Pitch_moment_due_to_elevators</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elev-lob-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 -0.2000
2.0000 -0.1000
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmde_rob">
<description>Pitch_moment_due_to_elevators</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elev-rob-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 -0.2000
2.0000 -0.1000
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmde_lib">
<description>Pitch_moment_due_to_elevators</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elev-lib-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 -0.2000
2.0000 -0.1000
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmde_rib">
<description>Pitch_moment_due_to_elevators</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elev-rib-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 -0.2000
2.0000 -0.1000
</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-aero-rad_sec</property>
<value>-21.00000</value><!-- -21.00000 -->
</product>
</function>
<function name="aero/coefficient/Cmadot">
<description>Pitch_moment_due_to_alpha_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>aero/alphadot-rad_sec</property>
<value>-16.0000</value><!-- -4.0000 doubled 2 times for better pitch response -->
</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>
<value>0.1200</value><!-- 1200 -->
</product>
</function>
<function name="aero/coefficient/Cnr">
<description>Yaw_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value>-0.3000</value><!-- -1500 -->
</product>
</function>
<function name="aero/coefficient/Cndr">
<description>Yaw_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value>-0.1000</value>
</product>
</function>
<function name="aero/coefficient/Cnda">
<description>Adverse_yaw</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<value>0.0000</value>
</product>
</function>
</axis>
</aerodynamics>