I tried values on aerodynamic table. But i don't have the real tables of Concorde. I made like i know how it behaves.
I saw in a documentary that at cruise, the engines have N1=96% and N2=84%, and that the angle of attack is aproximatively of 3°.
I'm on doubt if the Concorde can climb without balancing fuel, or if the lack of balancing just bring overconsuption. I saw that a flight with a certain angle of attack needs some constant triming.
I tried two aproaches. I kept the drag due to trim x10 as on first time. The first was to increase lift coefficient for the trimling would be at zero, so the plane can go supersonic only of we balance fuel. But the problem is that at Mach 2, the plane has no angle of attack (0°)
The second aproach is that the plane needs a certain angle of attack to fly, but it needs to trim up. But i decreased drastically the drag due to mach and the drag at zero lift. I increased a little the lift at mach 2 and zero AOA. I had a good result. The N1 and N2 is low as on the documentary, and the fuel consuption is at 4,5 tons/hour/engines. The only problem is that the AOA is too low, 1 or 2°. And in this case, the Concorde can reach supersonic cruise without balancing, but the fuel consuption is too high so that's a good thing.
I give you the aerodynamics part of Concorde.xml:
- Code: Select all
<aerodynamics>
<alphalimits unit="DEG">
<documentation>
added : => real -5.5 to 16.5 deg.
</documentation>
<min>-5.5</min>
<max>16.5</max>
</alphalimits>
<aero_ref_pt_shift_x>
<function name="aero/function/kC0">
<description>Shift_of_center_of_pressure</description>
<product>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.5 0.550
0.9 0.580
1.0 0.645
1.2 0.635
1.5 0.625
2.0 0.620
</tableData>
</table>
</product>
</function>
</aero_ref_pt_shift_x>
<documentation>
Added :
- additional lift on takeoff, otherwise tail touches the ground.
- downwash of the air between the wing and the ground creates a cushion,
making the landing smooth.
</documentation>
<function name="aero/function/kCLge">
<description>Change_in_lift_due_to_ground_effect</description>
<product>
<table>
<independentVar>aero/h_b-mac-ft</independentVar>
<tableData>
0.0000 1.2000
0.1000 1.1500
0.1500 1.0900
0.2000 1.0200
1.1000 1.0000
</tableData>
</table>
</product>
</function>
<axis name="DRAG">
<documentation>
Add Mach 0.0, 0.6, 1.1 and 1.4 :
- increase (x1.2) climb drag to get 10 pitch;
- increase (x1.2) landing drag to get 10 pitch and VREF 162 kt.
- supersonic decreases drag (in front of the wave);
- Mach 1.1 is end of transonic wall.
- Mach 1.4 is supersonic cruise.
</documentation>
<function name="aero/coefficient/CD0">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">velocities/mach</independentVar>
<tableData>
0.0000 0.6000 0.8000 1.1000 1.4000
-1.5700 1.5000 1.5000 1.5000 1.5000 1.5000
-0.2600 0.0408 0.0408 0.0340 0.0200 0.0060
0.0000 0.0204 0.0204 0.0170 0.0100 0.000
0.2600 0.0408 0.0408 0.0340 0.0200 0.0060
1.5700 1.5000 1.5000 1.5000 1.5000 1.5000
</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>0.042</value>
</product>
</function>
<documentation>
Add Mach 1.15, 1.3, 1.7 and 2.0 :
- respect the thrust X 2.7 by air intakes.
- supersonic decreases drag (in front of the wave).
- Mach 1.8 adjusts climb rate : 0.015 -> 0.018.
- Mach 2.0 adjusts consumption during supersonic cruise.
Climb from Mach 0.95 to 1.7 in 10 minutes, adjusted by :
- Mach 1.1 is end of transonic wall.
- Mach 1.3 is start of effect of air intakes.
- Mach 1.7 is end of reaheat.
</documentation>
<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>
0.0 0.000
0.79 0.000
1.1 0.023
1.15 0.020
1.3 0.019
1.7 0.016
1.8 0.010
2.0 0.002
</tableData>
</table>
</product>
</function>
<documentation>
nose drag.
</documentation>
<function name="aero/coefficient/CDflap">
<description>Drag_due_to_flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/flap-cmd-norm</property>
<value>0.0550</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/gear-pos-norm</property>
<value>0.0110</value>
</product>
</function>
<documentation>
0.0170 replaced by 0.0 : ctrl-B enables speedbrakes.
</documentation>
<function name="aero/coefficient/CDsb">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0.0</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>
<documentation>
- drag is always positiv.
- divide by 10.
-Default value 0.0055
</documentation>
<function name="aero/coefficient/CDde">
<description>Drag_due_to_Elevator_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<abs>
<property>fcs/elevator-pos-norm</property>
</abs>
<value>0.055</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>
<axis name="LIFT">
<documentation>
Add Mach 0.0 and 0.6 :
- decrease (0 and x1/3 at 0 radian) landing lift to get 10 pitch;
- decrease climb lift to get 10 pitch;
- at low speed, lift is better (x0.75) at high AOA, because of vortex over the wing.
Add Mach above 0.8 :
- transonic (Mach 1.06) shifts the curve vertically (XB-70).
- supersonic (above Mach 1.18) shifts the curve vertically (XB-70).
- adjust consumption during supersonic cruise : drag increases with alpha.
</documentation>
<function name="aero/coefficient/CLalpha">
<description>Lift_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">velocities/mach</independentVar>
<tableData>
0.0 0.6 0.8 1.0 1.06 1.18 1.65 2.10
-0.20 -0.227 -0.227 -0.680 -0.680 -0.700 -0.680 -0.780 -0.880
0.00 0.000 0.067 0.200 0.200 0.180 0.200 0.100 0.060
0.23 0.900 0.900 1.200 1.200 1.180 1.200 1.100 1.100
0.60 0.200 0.200 0.600 0.600 0.580 0.600 0.500 0.400
</tableData>
</table>
</product>
</function>
<documentation>
changed 1.5 to 0.0 : used flaps as nose.
</documentation>
<function name="aero/coefficient/dCLflap">
<description>Delta_Lift_due_to_flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/flap-cmd-norm</property>
<value>0.0000</value>
</product>
</function>
<documentation>
-0.0800 replaced by 0.0 : ctrl-B enables speedbrakes.
</documentation>
<function name="aero/coefficient/dCLsb">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0.0</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>0.2000</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>-0.1000</value>
</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>-0.4000</value>
</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>0.1500</value>
</product>
</function>
<function name="aero/coefficient/Clda">
<description>Roll_moment_due_to_aileron</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 0.1000
2.0000 0.0330
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cldr">
<description>Roll_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<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>-0.7000</value>
</product>
</function>
<function name="aero/coefficient/Cmde">
<description>Pitch_moment_due_to_elevator</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elevator-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 -1.3000
2.0000 -0.3250
</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>-21.0000</value>
</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>-4.0000</value>
</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>
</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>-0.1500</value>
</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>
If you want to try.
And i show you the part of the documentary i saw. If i don't have the right to post it, tell me.
https://youtu.be/BhbcH3pAPSI?t=776
So tell me what you think.
And for the Flight Engineer panel, i though about taking th model of roof panel switches and puting them on the place of the actual 2D switches, but i don't understand yet how the code works on the Panel and Model folder. :s