fix(a380x/flight model): A380X Flight Model Update plus fix auto-rotate issue

.github/CHANGELOG.md

@@ -105,7 +105,7 @@
 1. [A380/PFD] Add DISCONNECT AP FOR LDG FMA message - @BravoMike99 (bruno_pt99)
 1. [A380X/ENG] Adjust climb thrust to be more accurate - @BlueberryKing (BlueberryKing)
 1. [A380X/EWD] Show THR limit in EWD instead of N1 - @flogross89 (floridude)
-1. [A380X/FLIGHT MODEL] Fix pitchup and unrecoverable stall - - @donstim (donbikes#4084)
+1. [A380X/FLIGHT MODEL] Fix pitchup and unrecoverable stall - @donstim (donbikes#4084)
 1. [ATC/TCAS] Fixed TCAS failure on baro corrected altitude going invalid - @tracernz (Mike)
 1. [ATC/TCAS] Fixed TCAS slant range computation - @tracernz (Mike)
 1. [A380X] Add baro unit (hPa/in.Hg) auto selection - @tracernz (Mike)
@@ -150,6 +150,7 @@
 1. [A380X/FMS] Add STEP ALTs tab on VERT REV page & auto step climb functionality - @flogross89 (floridude)
 1. [A380X/FMS] Add selection of CLB/DES constraint if constraint type is unknown - @flogross89 (floridude)
 1. [FMS] Fix approach ident only showing on ND when approach is being flown - @BravoMike99 (bruno_pt99)
+1. [A380X/FLIGHT MODEL] General flight model update plus fix auto-rotate issue - @donstim (donbikes#4084)
 
 ## 0.12.0
 

fbw-a380x/src/base/flybywire-aircraft-a380-842/SimObjects/AirPlanes/FlyByWire_A380_842/flight_model.cfg

@@ -493,20 +493,20 @@ wing_span = 261.65 ; Wing span b (FEET)
 wing_root_chord = 58.86 ; Wing root chord croot (FEET), should be 57.97 but increased to match reference MAC length
 wing_camber = 1 ; (DEGREES) (Unkown - estimated value)
 wing_thickness_ratio = 0.05 ; Local thickness is local_chord(x)*wing_thickness_ratio, x = lateral coord
-wing_dihedral = 6.5 ; Dihedral angle Lambda (DEGREES)
+wing_dihedral = 5.6 ; Dihedral angle Lambda (DEGREES)
 wing_incidence = 2 ; Wing incidence (DEGREES) (unknown)
 wing_twist = -5.5 ; Wing twist epsilon (DEGREES)
 oswald_efficiency_factor = 0.70 ; Wing Oswald efficiency factor e (non dimensional)
 wing_winglets_flag = 0 ; Has winglets true/false
-wing_sweep = 37 ; Wing sweep (DEGREES)
+wing_sweep = 33.5 ; Wing sweep (DEGREES)
 ;wing_pos_apex_lon = 0 ; Longitudinal (z) position of wing apex w.r.t reference datum (FEET) (not used)
 wing_pos_apex_vert = -2 ; Vertical (y) position of wing apex w.r.t reference datum (FEET)
-htail_area = 1250 ; Horizontal tail area (SQUARE FEET) 
+htail_area = 1000 ; Horizontal tail area (SQUARE FEET) 
 htail_span = 80 ; Horizontal tail span (FEET) 
 htail_pos_lon = -105 ; Longitudinal (z) position of horizontal tail  w.r.t reference datum (FEET)
 htail_pos_vert = 13.8 ; Vertical (y) position of horizontal tail  w.r.t reference datum (FEET)
 htail_incidence = -2 ; Horizontal tail incidence (DEGREES) 
-htail_sweep = 38 ; Horizontal tail sweep angle (DEGREES)
+htail_sweep = 30 ; Horizontal tail sweep angle (DEGREES)
 htail_thickness_ratio = 0.02 ; Local thickness is local_chord(x)*htail_thickness_ratio, x = lateral coord
 vtail_area = 2800.4 ; Vertical tail area (SQUARE FEET)
 vtail_span = 40.87 ; Vertical tail span (FEET)
@@ -551,7 +551,7 @@ fly_by_wire = 0 ; Fly-by-wire available true/false
 elevator_elasticity_table = 0:1, 400:1
 aileron_elasticity_table = 0:1, 400:1
 rudder_elasticity_table = 0:1, 400:1
-elevator_trim_elasticity_table = 0:0.3, 40:0.50, 55:1.2, 80:1.45, 400:1.7
+elevator_trim_elasticity_table =  0:0.25, 40:0.38, 55:1.1, 80:1.3, 400:1.8
 ;controls_reactivity_scalar = 1 ; Reactivity scalar for all controls
 
 
@@ -560,12 +560,12 @@ lift_coef_pitch_rate = -47.338 ; The change in lift per change in pitch rate
 lift_coef_daoa = 0 ; lift per change in angle of attack rate
 lift_coef_delta_elevator = -1.143 ; The change in lift per change in elevator deflection
 lift_coef_horizontal_incidence = 0 ; The change in lift per change in horizontal incidence angle
-lift_coef_flaps = 1.505 ; Change in lift due to flaps
+lift_coef_flaps = 1.3043 ; Change in lift due to flaps
 lift_coef_spoilers = -0.546875 ; Change in lift due to spoilers
-drag_coef_zero_lift = 0.0249 ; The zero lift drag polar
-drag_coef_flaps = 0.0706
-drag_coef_gear = 0.079
-drag_coef_spoilers = 0.04775;  ; Change in drag due to spoilers
+drag_coef_zero_lift = 0.02491 ; The zero lift drag polar
+drag_coef_flaps = 0.274
+drag_coef_gear = 0.019
+drag_coef_spoilers = 0.025;  ; Change in drag due to spoilers
 side_force_slip_angle = -0.624 ; (yaw angle) The change in side force per change in side slip angle
 side_force_roll_rate = 2.069 ; (roll velocity)  The change in side force per change in roll rate
 side_force_yaw_rate = 8.646 ; (yaw velocity) The change in side force per change in yaw rate
@@ -598,8 +598,8 @@ yaw_moment_delta_rudder_propwash = 0.753 ; (control)
 yaw_moment_delta_rudder_trim_scalar = 0.753 ; Change in yaw moment due to rudder trim
 compute_aero_center = 0
 aero_center_lift = 11 ; Init to center
-lift_coef_aoa_table = -3.15:0, 0:0.138, 0.139:1.32, 0.2:1.48, 0.314:1.90, 0.36:1.740, 0.5:1.50, 3.15:0
-lift_coef_ground_effect_mach_table = 0:0.75, 0.1:0.73, 0.2:0.69, 0.3:0.68, 0.4:0.66, 0.5:0.65, 1.0:0.63
+lift_coef_aoa_table = -3.15:0, 0:0.210, 0.139:1.01, 0.2:1.24, 0.314:1.60, 0.36:1.70, 0.5:1.58, 3.15:0
+lift_coef_ground_effect_mach_table = 0:0.71, 0.1:0.69, 0.2:0.68, 0.3:0.67, 0.4:0.66, 0.5:0.64, 1.0:0.60
 lift_coef_mach_table = 0:1
 lift_coef_delta_elevator_mach_table = 0:0
 lift_coef_daoa_mach_table = 0:0
@@ -646,26 +646,26 @@ lift_coef_at_drag_zero = 0.12500
 lift_coef_at_drag_zero_flaps = 0.40000
 ;elevator_lift_coef = 0.5 ; Defines elevator lift vs elevator angle-of-attack
 ;rudder_lift_coef = 0.5 ; Defines rudder lift vs rudder angle-of-attack
-;fuselage_lateral_cx = 0.5; Defines fuselage lift and side force vs fuselage angle-of-attack and beta
+fuselage_lateral_cx = 0.5; Defines fuselage lift and side force vs fuselage angle-of-attack and beta
 StallDef_StartRatio = 4
 StallDef_EndRatio = 6
 StallDef_airflowdetachspeed = 0.01
 Stall_AileronAddIncidence = 7
 Stall_TipAddIncidence = 7
-presspt_fwd_Alpha0_pMAC = -0.15  ; Forward offset for wing center of pressure at aoa = 0 -- is ratio of local MAC -- positive is forward, negative is aft
-presspt_fwd_AlphaStall_pMAC = -0.5  ; ; Forward offset for wing center of pressure at stall aoa -- is ratio of local MAC -- positive is forward, negative is aft
+presspt_fwd_Alpha0_pMAC = -0.42  ; Forward offset for wing center of pressure at aoa = 0 -- is ratio of local MAC -- positive is forward, negative is aft
+presspt_fwd_AlphaStall_pMAC = -0.4  ; ; Forward offset for wing center of pressure at stall aoa -- is ratio of local MAC -- positive is forward, negative is aft
 
 [FLIGHT_TUNING]
 
 modern_fm_only = 1; 1 (true) forces use of modern flight model regardless of what user selected in MSFS options menu. 0 (false) allows use of user-selected flight model
 ;empty_cg_deviation_limit = 20 ; Maximum deviation of empty weight cg allowed in wegiht & balance UI menu (in feet)
 ;icing_scalar = 1 ; Scales effect of icing on lift and weight
-cruise_lift_scalar = 0.81
+cruise_lift_scalar = 1.00
 parasite_drag_scalar = 1
-induced_drag_scalar = 0.827
-flap_induced_drag_scalar = 0.25
+induced_drag_scalar = 0.603
+flap_induced_drag_scalar = 0.35
 elevator_effectiveness = 1
-elevator_maxangle_scalar = 0.7
+elevator_maxangle_scalar = 1
 aileron_effectiveness = 1
 rudder_effectiveness = 0.25
 rudder_maxangle_scalar = 1
@@ -675,7 +675,7 @@ yaw_stability = 1
 pitch_gyro_stability = 6
 roll_gyro_stability = 4.5
 yaw_gyro_stability = 1
-elevator_trim_effectiveness = 1.1
+elevator_trim_effectiveness = 1
 aileron_trim_effectiveness = 1
 rudder_trim_effectiveness = 1
 hi_alpha_on_roll = 0
@@ -804,12 +804,14 @@ lift_scalar = 1 ; Scalar coefficient to ponderate global flap lift coef (non dim
 drag_scalar = 1 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned)
 pitch_scalar = 1 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned)
 max_on_ground_position = 5 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found.
-flaps-position.0 =  0.00,  -1, 0, 0.0 ; CONF 0
-flaps-position.1 =  5.0,  -1, 0.05, 0.01 ; CONF 1
-flaps-position.2 = 10.00, 222, 0.22, 1.26 ; CONF 1+F
-flaps-position.3 = 15.00, 220, 1.00, 1.30 ; CONF 2
-flaps-position.4 = 20.00, 196, 1.50, 1.46; CONF 3
-flaps-position.5 = 32.00, 182, 1.00, 1.00 ; CONF FULL
+; Flap position parameters - flap position (degrees), airspeed limit (knots), drag scalar, lift scalar, area scalar, add camber (radians) - raises maximum lift coefficient, add aft feet - sets center of lift, where a postive value moves the center of lift forward (generating more pitch up) and a negative value will move it back (generating more pitch down), add incidence - defines now much of the additional lift is applied at 0 degrees AOA. At 1 (100%), the additional lift is added as a constant over the entire AOA range. When set to 0.5 (the default value), 50% of the additional lift is applied at 0 degrees AOA and 100% is added at the stall AOA.
+flaps-position.0 =  0.00,  -1, 0.00, 0.00, 1.00, 0.00,  0.00, 1.00 ; CONF 0
+flaps-position.1 =  5.00,  -1, 0.05, 0.01, 1.00, 0.00,  0.00, 1.00 ; CONF 1
+flaps-position.2 = 10.00, 222, 0.68, 0.30, 1.00, 0.00,  4.00, 1.00 ; CONF 1+F 0.31
+flaps-position.3 = 15.00, 220, 0.76, 0.43, 1.00, 0.005,  6.50, 1.00 ; CONF 2  
+flaps-position.4 = 20.00, 196, 1.34, 1.266, 1.02, 0.01,  9.00, 1.00; CONF 3  1.37
+flaps-position.5 = 32.00, 182, 1.00, 1.00, 1.03, 0.015, 10.00, 1.00 ; CONF FULL
+
 
 [FLAPS.2]
 type = 2 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge
@@ -820,13 +822,13 @@ damaging-speed = 260 ; Speed above which flap is damaged (Kts)
 blowout-speed = 270 ; Speed above which flap is blown out (Kts)
 maneuvering_flaps = 0
 ;delay_between_flap_index = 0
-lift_scalar = 0.01 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
+lift_scalar = 1 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
 drag_scalar = 0.5 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned)
 pitch_scalar = 1 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned)
 max_on_ground_position = 5 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found.
-flaps-position.0 =  0.00,  -1, 1.00, 1.00 ; CONF 0
-flaps-position.1 = 20.00, 263, 0.10, 0.01 ; CONF 1
-flaps-position.2 = 20.01, 222, 1.00, 1.00 ; CONF 1+F
-flaps-position.3 = 20.02, 220, 1.00, 1.25 ; CONF 2
-flaps-position.4 = 23.00, 196, 1.50, 1.25 ; CONF 3
-flaps-position.5 = 23.01, 182, 1.00, 1.00 ; CONF FULL
+flaps-position.0 =  0.00,  -1, 1.00, 1.00, 1.00, 0.00, 0.00, 0.00 ; CONF 0
+flaps-position.1 = 20.00, 263, 0.10, 0.10, 1.00, 0.006, 0.00, 0.00 ; CONF 1
+flaps-position.2 = 20.01, 222, 0.69, 0.305, 1.00, 0.006, 0.00, 0.00 ; CONF 1+F 0.30
+flaps-position.3 = 20.02, 220, 0.76, 0.43, 1.00, 0.006, 0.00, 0.00 ; CONF 2 
+flaps-position.4 = 23.00, 196, 1.33, 1.266, 1.00, 0.01, 0.00, 0.00 ; CONF 3   1.36
+flaps-position.5 = 23.01, 182, 1.00, 1.00, 1.00, 0.01, 0.00, 0.00 ; CONF FULL