rework(flight_model): initial

Author: Revyn112

hdw-a333x/src/base/headwindsim-aircraft-a330-300/SimObjects/Airplanes/Headwind_A330_300/flight_model.cfg

@@ -5,14 +5,14 @@ minor = 0
 [WEIGHT_AND_BALANCE]
 max_gross_weight = 518086 ; Maximum takeoff weight, (LBS)
 empty_weight = 271168 ; Empty weight, (LBS); Includes weight to account for crew, pantry, galleys, lavs, potable water, emergency equipment etc.
-reference_datum_position = 0, 0, 0
+reference_datum_position = 0, 0, 0 ; Position of reference datum relative to FS(0,0,0) (FEET), z, x, y
 ; adjust empty weight CG position to ensure 26.2% MAC at Empty Weight
-empty_weight_CG_position = -28.276, 0, 0 ; Position of airplane empty weight CG relative to reference datum (FEET), z, x, y
+empty_weight_CG_position = -27.56, 0, 0 ; Position of airplane empty weight CG relative to reference datum (FEET), z, x, y
 CG_forward_limit = 0.15 ; Gravity center forward limit (longitudinal offset) for longitudinal stability
 CG_aft_limit = 0.41 ; Gravity center after limit (longitudinal offset z) w.r.t reference datum for longitudinal stability (FEET)
-empty_weight_pitch_MOI = 28163472 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET)
-empty_weight_roll_MOI = 9217827 ; Empty roll moment of inertia, Jzz (SLUG SQ FEET)
-empty_weight_yaw_MOI = 36117016 ; Empty yaw moment of inertia, Jyy (SLUG SQ FEET)
+empty_weight_pitch_MOI = 23228924 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET)
+empty_weight_roll_MOI = 14300433 ; Empty roll moment of inertia, Jzz (SLUG SQ FEET)
+empty_weight_yaw_MOI = 35047716 ; Empty yaw moment of inertia, Jyy (SLUG SQ FEET)
 empty_weight_coupled_MOI = 10000 ; Empty transverse moment of inertia, Jyz (SLUG SQ FEET)
 activate_mach_limit_based_on_cg = 0 ; Activate mach limitation depending on CG position (true if > 0 /false othewise). Mostly for Concorde).
 activate_cg_limit_based_on_mach = 0 ; Activate cg limitation depending on mach value (true if > 0 /false othewise). Mostly for Concorde).
@@ -23,7 +23,7 @@ activate_cg_limit_based_on_mach = 0 ; Activate cg limitation depending on mach v
 ; MZFW = 173000 kg/381400 lbs
 ; OEW = 123000 kg/271168 lbs
 ; Max Payload = 44836 kg/98846 lbs
-; Max Fuel = 97530 ltrs (111665 kg)/36743 us gal (246179 lbs) @ specific gravity of 0.8 ISA conditions
+; Max Fuel = 139087 ltrs (111665 kg)/36743 us gal (246179 lbs) @ specific gravity of 0.8 ISA conditions
 ; Average Adult pax assumed to be 185lbs/84kg
 ; Passenger baggage weight of 20 kg/pax is also added, making total pax + baggage weight = 104 kg/pax (i.e. Passenger weight on Simbrief)
 ; Starting load is 0% of capacity
@@ -177,7 +177,7 @@ Trigger.10 = Name:CloseLeftOuterTankValves5MinAfterLowFuelLevel#Target:LeftOuter
 Trigger.11 = Name:CloseRightOuterTankValves5MinAfterLowFuelLevel#Target:LeftOuter#Threshold:1#Condition:TankQuantityBelow#DelayTrue:300#EffectTrue:CloseValve.RightTransferValve1,CloseValve.RightTransferValve2
 
 [AIRPLANE_GEOMETRY]
-aileron_area=160.60
+aileron_area=200
 aileron_down_limit=25
 aileron_elasticity_table = 0:1, 400:1 ;; A32NX PR #5842
 aileron_to_rudder_scale=0
@@ -187,7 +187,7 @@ air_spoiler_limit=45
 auto_spoiler_auto_retracts=0
 auto_spoiler_available=0
 auto_spoiler_min_speed=72
-elevator_area=211.40
+elevator_area=300
 elevator_down_limit=17
 elevator_elasticity_table = 0:1, 400:1 ;; A32NX PR #7516
 elevator_trim_elasticity_table= 0:0.3, 100:0.35, 120:1, 400:1
@@ -197,15 +197,15 @@ elevator_trim_neutral=0
 elevator_up_limit=25
 flap_to_aileron_scale=0
 fly_by_wire=0
-fuselage_center_pos=-24.987358, 0, 3.121224
-fuselage_diameter=18.5
-fuselage_length=208.86
-htail_area = 883.29
-htail_incidence=0
+fuselage_center_pos=-26.0, 0, 2.5
+fuselage_diameter=9.25
+fuselage_length=204.0
+htail_area = 900
+htail_incidence= 0
 htail_pos_lon = -120
 htail_pos_vert = 10
 htail_span = 63.65
-htail_sweep= 32
+htail_sweep=32
 htail_thickness_ratio=0.02
 load_safety_factor=1.5
 min_ailerons_for_spoilerons=5
@@ -215,29 +215,29 @@ negative_g_limit_flaps_up=-1
 oswald_efficiency_factor=0.72
 positive_g_limit_flaps_down=2
 positive_g_limit_flaps_up=2.5
-rudder_area=116.14
+rudder_area=250
 rudder_elasticity_table=0:1, 85:1, 110:0.7, 445:0.136
 rudder_limit=25
 rudder_trim_limit = 0 ; Rudder trim max deflection angle (absolute value) (DEGREES)
 spoiler_extension_time=0.1
 spoiler_handle_available=1
 spoiler_limit=45
 spoilerons_available=0
-vtail_area=486.85
-vtail_pos_lon=-107
-vtail_pos_vert=23.5
-vtail_span=28.87
-vtail_sweep=43
-vtail_thickness_ratio=0.028
-wing_area=3892.23
-wing_camber=3
-wing_dihedral=8
-wing_incidence=0
-wing_pos_apex_lon=25.193029
+vtail_area=1000
+vtail_pos_lon=-108
+vtail_pos_vert=25
+vtail_span=27.2
+vtail_sweep=45
+vtail_thickness_ratio=0.02
+wing_area=3500
+wing_camber=1
+wing_dihedral=5
+wing_incidence=2
+wing_pos_apex_lon=-50 ; NOT USED
 wing_pos_apex_vert=-2.8
-wing_root_chord=34.61
+wing_root_chord=70
 wing_span=209.97
-wing_sweep=30
+wing_sweep=33
 wing_thickness_ratio=0.03
 wing_twist=-1
 wing_winglets_flag = 1 ; Has winglets true/false (not currently used by MSFS)
@@ -250,7 +250,7 @@ lift_coef_delta_elevator = -1.652 ; The change in lift per change in elevator de
 lift_coef_horizontal_incidence = 0 ; The change in lift per change in horizontal incidence angle
 lift_coef_flaps = 1.2 ; Change in lift due to flaps
 lift_coef_spoilers = -0.25 ; Change in lift due to spoilers- Full extension at MMO/VMO -0.34, at M0.90 0, Ground spoilers -0.60, Partial ground spoilers -0.425
-drag_coef_zero_lift = 0.0200 ; The zero lift drag polar
+drag_coef_zero_lift = 0.0280 ; The zero lift drag polar
 drag_coef_flaps = 0.0602
 drag_coef_gear = 0.030
 drag_coef_spoilers = 0.05775;  Change in drag due to spoilers
@@ -285,7 +285,7 @@ yaw_moment_delta_rudder = 1.321 ; (control)The change in yaw moment per change i
 yaw_moment_delta_rudder_propwash = 1.321 ; (control)
 yaw_moment_delta_rudder_trim_scalar = 1.321 ; Change in yaw moment due to rudder trim
 compute_aero_center = 0
-aero_center_lift = -28.0 ; Init to center
+aero_center_lift = -27.0 ; Init to center
 lift_coef_aoa_table = -3.150000:0.000000, 0.000000:0.224000, 0.139000:1.390000, 0.200000:1.480000, 0.260000:1.760000, 0.290000:1.750000, 0.320000:1.600000, 0.500000:1.500000, 3.150000:0.000000
 lift_coef_ground_effect_mach_table = 0.0:1.178, 0.15:1.178, 0.19:1.178, 0.20:1.176, 0.22:1.173, 0.25:1.17, 0.27:1.1675, 0.30:1.164, 0.35:1.159, 1.0:1
 lift_coef_mach_table = 0:1

hdw-a333x/src/base/headwindsim-aircraft-a330-300/SimObjects/Airplanes/Headwind_A330_300/target_performance.cfg

@@ -48,15 +48,15 @@ full_flap_max_vert_dive_speed_0pctpower = 511.8,1;
 no_flap_max_flat_fall_speed_0pctpower = 143.1,1;
 
 [DOUBLE_CHECKS]
-wing_area = 1313.0,0.1;
-wing_span = 117.45,0.1;
-htail_area = 67.10,0.1;
-htail_span = 22.3,0.1;
-vtail_area = 55.0,0.1;
-vtail_span = 7.5,0.1;
-max_gross_weight = 507063,1.0;
-empty_weight = 266760,1.0;
-max_hp = 37828,0.1;
+wing_area = 3500.0,0.1;
+wing_span = 209.97,0.1;
+htail_area = 900,0.1;
+htail_span = 63.65,0.1;
+vtail_area = 1000.0,0.1;
+vtail_span = 27.2,0.1;
+max_gross_weight = 553360,1.0;
+empty_weight = 279987,1.0;
+max_hp = 1631,0.1;
 
 [PERFORMANCE_REPORT]
 //file_path="C:\Users\golivier\Desktop\JUNK_MESH\perf_report.csv"

hdw-a333x/src/base/headwindsim-aircraft-a330-300/html_ui/Pages/A333X_Core/A32NX_PayloadManager.js

@@ -134,11 +134,11 @@ const MAX_SEAT_AVAILABLE = 436;
  * Calculate %MAC ZWFCG of all stations
  */
 function getZfwcg() {
-    const leMacZ = -22.20; // Accurate to 3 decimals, replaces debug weight values
-    const macSize = 23.19; // Accurate to 3 decimals, replaces debug weight values
+    const leMacZ = -15.33; // Accurate to 3 decimals, replaces debug weight values
+    const macSize = 46.69; // Accurate to 3 decimals, replaces debug weight values
 
     const emptyWeight = (SimVar.GetSimVarValue("EMPTY WEIGHT", getUserUnit()));
-    const emptyPosition = -28.276; // Value from flight_model.cfg
+    const emptyPosition = -27.56; // Value from flight_model.cfg
     const emptyMoment = emptyPosition * emptyWeight;
     const PAX_WEIGHT = SimVar.GetSimVarValue("L:A32NX_WB_PER_PAX_WEIGHT", "Number");
 

hdw-a333x/src/systems/fmgc/src/guidance/vnav/FlightModel.ts

@@ -2,13 +2,13 @@ import { MathUtils } from '@flybywiresim/fbw-sdk';
 import { Common, FlapConf } from './common';
 
 export class FlightModel {
-    static Cd0 = 0.026;
+    static Cd0 = 0.0280;
 
-    static wingSpan = 197.83;
+    static wingSpan = 209.97;
 
-    static wingArea = 3892.23;
+    static wingArea = 3500.00;
 
-    static wingEffcyFactor = 0.9199;
+    static wingEffcyFactor = 0.72;
 
     static requiredAccelRateKNS = 1.33; // in knots/second
 

hdw-a333x/src/systems/instruments/src/EFB/Ground/Pages/Payload/A330_343/a333x.json

@@ -1,9 +1,9 @@
 {
     "specs": {
         "prefix": "A333X",
-        "emptyPosition": -28.276,
-        "macSize": 23.19,
-        "leMacZ": -22.20,
+        "emptyPosition": -27.56,
+        "macSize": 46.69,
+        "leMacZ": -15.33,
         "weights": {
             "maxGw": 235000,
             "maxZfw": 173000,

hdw-a333x/src/wasm/fadec_a330/src/RegPolynomials.h

@@ -187,15 +187,16 @@ class Polynomial {
   /// </summary>
   double correctedEGT(double cn1, double cff, double mach, double alt) {
     double outCEGT = 0;
-    cff = cff / 2;  // to account for the A380 double fuel flow. Will have to be taken care of
+    double cff_a330 = 2.7;
 
-    double c_EGT[16] = {3.2636e+02,  0.0000e+00, 9.2893e-01, 3.9505e-02,  3.9070e+02, -4.7911e-04, 7.7679e-03,  5.8361e-05,
-                        -2.5566e+00, 5.1227e-06, 1.0178e-07, -7.4602e-03, 1.2106e-07, -5.1639e+01, -2.7356e-03, 1.9312e-08};
+    double c_EGT[16] = {443.3145034,    0.0000000e+00, 3.0141710e+00,  3.9132758e-02, -4.8488279e+02, -1.2890964e-03,
+                        -2.2332050e-02, 8.3849683e-05, 6.0478647e+00,  6.9171710e-05, -6.5369271e-07, -8.1438322e-03,
+                        -5.1229403e-07, 7.4657497e+01, -4.6016728e-03, 2.8637860e-08};
 
-    outCEGT = c_EGT[0] + c_EGT[1] + (c_EGT[2] * cn1) + (c_EGT[3] * cff) + (c_EGT[4] * mach) + (c_EGT[5] * alt) +
-              (c_EGT[6] * powFBW(cn1, 2)) + (c_EGT[7] * cn1 * cff) + (c_EGT[8] * cn1 * mach) + (c_EGT[9] * cn1 * alt) +
-              (c_EGT[10] * powFBW(cff, 2)) + (c_EGT[11] * mach * cff) + (c_EGT[12] * cff * alt) + (c_EGT[13] * powFBW(mach, 2)) +
-              (c_EGT[14] * mach * alt) + (c_EGT[15] * powFBW(alt, 2));
+    outCEGT = c_EGT[0] + c_EGT[1] + (c_EGT[2] * cn1) + (c_EGT[3] * cff_a330) + (c_EGT[4] * mach) + (c_EGT[5] * alt) +
+              (c_EGT[6] * powFBW(cn1, 2)) + (c_EGT[7] * cn1 * cff_a330) + (c_EGT[8] * cn1 * mach) + (c_EGT[9] * cn1 * alt) +
+              (c_EGT[10] * powFBW(cff_a330, 2)) + (c_EGT[11] * mach * cff_a330) + (c_EGT[12] * cff_a330 * alt) +
+              (c_EGT[13] * powFBW(mach, 2)) + (c_EGT[14] * mach * alt) + (c_EGT[15] * powFBW(alt, 2));
 
     return outCEGT;
   }
@@ -205,10 +206,11 @@ class Polynomial {
   /// </summary>
   double correctedFuelFlow(double cn1, double mach, double alt) {
     double outCFF = 0;
+    double a330_f = 2.7;
 
-    double c_Flow[21] = {-1.7630e+02, -2.1542e-01, 4.7119e+01,  6.1519e+02,  1.8047e-03, -4.4554e-01, -4.3940e+01,
-                         4.0459e-05,  -3.2912e+01, -6.2894e-03, -1.2544e-07, 1.0938e-02, 4.0936e-01,  -5.5841e-06,
-                         -2.3829e+01, 9.3269e-04,  2.0273e-11,  -2.4100e+02, 1.4171e-02, -9.5581e-07, 1.2728e-11};
+    double c_Flow[21] = {-639.6602981, 0.00000e+00,  1.03705e+02,  -2.23264e+03, 5.70316e-03, -2.29404e+00, 1.08230e+02,
+                         2.77667e-04,  -6.17180e+02, -7.20713e-02, 2.19013e-07,  2.49418e-02, -7.31662e-01, -1.00003e-05,
+                         -3.79466e+01, 1.34552e-03,  5.72612e-09,  -2.71950e+02, 8.58469e-02, -2.72912e-06, 2.02928e-11};
 
     outCFF = c_Flow[0] + c_Flow[1] + (c_Flow[2] * cn1) + (c_Flow[3] * mach) + (c_Flow[4] * alt) + (c_Flow[5] * powFBW(cn1, 2)) +
              (c_Flow[6] * cn1 * mach) + (c_Flow[7] * cn1 * alt) + (c_Flow[8] * powFBW(mach, 2)) + (c_Flow[9] * mach * alt) +
@@ -217,7 +219,7 @@ class Polynomial {
              (c_Flow[16] * cn1 * powFBW(alt, 2)) + (c_Flow[17] * powFBW(mach, 3)) + (c_Flow[18] * powFBW(mach, 2) * alt) +
              (c_Flow[19] * mach * powFBW(alt, 2)) + (c_Flow[20] * powFBW(alt, 3));
 
-    return 2 * outCFF;
+    return outCFF * a330_f;
   }
 
   double oilTemperature(double energy, double preOilTemp, double maxOilTemp, double deltaTime) {

hdw-a333x/src/wasm/systems/a320_systems/src/airframe/mod.rs

@@ -17,10 +17,10 @@ pub struct A320Airframe {
 impl A320Airframe {
     const LOADSHEET: LoadsheetInfo = LoadsheetInfo {
         operating_empty_weight_kg: 123000.,
-        operating_empty_position: (-28.276, 0., 0.),
+        operating_empty_position: (-27.56, 0., 0.),
         per_pax_weight_kg: 84.,
-        mean_aerodynamic_chord_size: 23.19,
-        leading_edge_mean_aerodynamic_chord: -22.20,
+        mean_aerodynamic_chord_size: 46.69,
+        leading_edge_mean_aerodynamic_chord: -15.33,
     };
 
     pub fn new(context: &mut InitContext) -> Self {

hdw-a339x-acj/src/wasm/systems/a320_systems/src/airframe/mod.rs

@@ -17,10 +17,10 @@ pub struct A320Airframe {
 impl A320Airframe {
     const LOADSHEET: LoadsheetInfo = LoadsheetInfo {
         operating_empty_weight_kg: 134500.,
-        operating_empty_position: (-28.276, 0., 0.),
+        operating_empty_position: (-27.56, 0., 0.),
         per_pax_weight_kg: 84.,
-        mean_aerodynamic_chord_size: 23.19,
-        leading_edge_mean_aerodynamic_chord: -22.20,
+        mean_aerodynamic_chord_size: 46.69,
+        leading_edge_mean_aerodynamic_chord: -15.33,
     };
 
     pub fn new(context: &mut InitContext) -> Self {

hdw-a339x/src/base/headwindsim-aircraft-a330-900/SimObjects/Airplanes/Headwind_A330neo/flight_model.cfg

@@ -7,10 +7,10 @@ max_gross_weight = 553360 ; Maximum takeoff weight, (LBS)
 empty_weight = 279987 ; Empty weight, (LBS); Includes weight to account for crew, pantry, galleys, lavs, potable water, emergency equipment etc.
 reference_datum_position = 0, 0, 0 ; Position of reference datum relative to FS(0,0,0) (FEET), z, x, y
 ; adjust empty weight CG position to ensure 26.2% MAC at Empty Weight
-empty_weight_CG_position = -28.276, 0, 0 ; Position of airplane empty weight CG relative to reference datum (FEET), z, x, y
+empty_weight_CG_position = -27.56, 0, 0 ; Position of airplane empty weight CG relative to reference datum (FEET), z, x, y
 CG_forward_limit = 0.15 ; Gravity center forward limit (longitudinal offset) for longitudinal stability
 CG_aft_limit = 0.41 ; Gravity center after limit (longitudinal offset z) w.r.t reference datum for longitudinal stability (FEET)
-empty_weight_pitch_MOI = 23228392 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET)
+empty_weight_pitch_MOI = 23228924 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET)
 empty_weight_roll_MOI = 14300433 ; Empty roll moment of inertia, Jzz (SLUG SQ FEET)
 empty_weight_yaw_MOI = 35047716 ; Empty yaw moment of inertia, Jyy (SLUG SQ FEET)
 empty_weight_coupled_MOI = 10000 ; Empty transverse moment of inertia, Jyz (SLUG SQ FEET)
@@ -177,7 +177,7 @@ Trigger.10 = Name:CloseLeftOuterTankValves5MinAfterLowFuelLevel#Target:LeftOuter
 Trigger.11 = Name:CloseRightOuterTankValves5MinAfterLowFuelLevel#Target:LeftOuter#Threshold:1#Condition:TankQuantityBelow#DelayTrue:300#EffectTrue:CloseValve.RightTransferValve1,CloseValve.RightTransferValve2
 
 [AIRPLANE_GEOMETRY]
-aileron_area=160.60
+aileron_area=200
 aileron_down_limit=25
 aileron_elasticity_table = 0:1, 400:1 ;; A32NX PR #5842
 aileron_to_rudder_scale=0
@@ -187,7 +187,7 @@ air_spoiler_limit=45
 auto_spoiler_auto_retracts=0
 auto_spoiler_available=0
 auto_spoiler_min_speed=72
-elevator_area=211.40
+elevator_area=300
 elevator_down_limit=17
 elevator_elasticity_table = 0:1, 400:1 ;; A32NX PR #7516
 elevator_trim_elasticity_table= 0:0.3, 100:0.35, 120:1, 400:1
@@ -197,15 +197,15 @@ elevator_trim_neutral=0
 elevator_up_limit=25
 flap_to_aileron_scale=0
 fly_by_wire=0
-fuselage_center_pos=-24.987358, 0, 3.121224
-fuselage_diameter=18.5
-fuselage_length=208.86
-htail_area = 883.29
-htail_incidence=0
+fuselage_center_pos=-26.0, 0, 2.5
+fuselage_diameter=9.25
+fuselage_length=204.0
+htail_area = 900
+htail_incidence= 0
 htail_pos_lon = -120
 htail_pos_vert = 10
 htail_span = 63.65
-htail_sweep= 32
+htail_sweep=32
 htail_thickness_ratio=0.02
 load_safety_factor=1.5
 min_ailerons_for_spoilerons=5
@@ -215,29 +215,29 @@ negative_g_limit_flaps_up=-1
 oswald_efficiency_factor=0.72
 positive_g_limit_flaps_down=2
 positive_g_limit_flaps_up=2.5
-rudder_area=116.14
+rudder_area=250
 rudder_elasticity_table=0:1, 85:1, 110:0.7, 445:0.136
 rudder_limit=25
 rudder_trim_limit = 0 ; Rudder trim max deflection angle (absolute value) (DEGREES)
 spoiler_extension_time=0.1
 spoiler_handle_available=1
 spoiler_limit=45
 spoilerons_available=0
-vtail_area=486.85
-vtail_pos_lon=-107
-vtail_pos_vert=23.5
-vtail_span=28.87
-vtail_sweep=43
-vtail_thickness_ratio=0.028
-wing_area=3892.23
-wing_camber=3
-wing_dihedral=8
-wing_incidence=0
-wing_pos_apex_lon=25.193029
+vtail_area=1000
+vtail_pos_lon=-108
+vtail_pos_vert=25
+vtail_span=27.2
+vtail_sweep=45
+vtail_thickness_ratio=0.02
+wing_area=3500
+wing_camber=1
+wing_dihedral=5
+wing_incidence=2
+wing_pos_apex_lon=-50 ; NOT USED
 wing_pos_apex_vert=-2.8
-wing_root_chord=34.61
+wing_root_chord=70
 wing_span=209.97
-wing_sweep=30
+wing_sweep=33
 wing_thickness_ratio=0.03
 wing_twist=-1
 wing_winglets_flag = 1 ; Has winglets true/false (not currently used by MSFS)
@@ -250,7 +250,7 @@ lift_coef_delta_elevator = -1.652 ; The change in lift per change in elevator de
 lift_coef_horizontal_incidence = 0 ; The change in lift per change in horizontal incidence angle
 lift_coef_flaps = 1.2 ; Change in lift due to flaps
 lift_coef_spoilers = -0.25 ; Change in lift due to spoilers- Full extension at MMO/VMO -0.34, at M0.90 0, Ground spoilers -0.60, Partial ground spoilers -0.425
-drag_coef_zero_lift = 0.0200 ; The zero lift drag polar
+drag_coef_zero_lift = 0.0280 ; The zero lift drag polar
 drag_coef_flaps = 0.0602
 drag_coef_gear = 0.030
 drag_coef_spoilers = 0.05775;  Change in drag due to spoilers
@@ -285,7 +285,7 @@ yaw_moment_delta_rudder = 1.321 ; (control)The change in yaw moment per change i
 yaw_moment_delta_rudder_propwash = 1.321 ; (control)
 yaw_moment_delta_rudder_trim_scalar = 1.321 ; Change in yaw moment due to rudder trim
 compute_aero_center = 0
-aero_center_lift = -28.0 ; Init to center
+aero_center_lift = -27.0 ; Init to center
 lift_coef_aoa_table = -3.150000:0.000000, 0.000000:0.224000, 0.139000:1.390000, 0.200000:1.480000, 0.260000:1.760000, 0.290000:1.750000, 0.320000:1.600000, 0.500000:1.500000, 3.150000:0.000000
 lift_coef_ground_effect_mach_table = 0.0:1.178, 0.15:1.178, 0.19:1.178, 0.20:1.176, 0.22:1.173, 0.25:1.17, 0.27:1.1675, 0.30:1.164, 0.35:1.159, 1.0:1
 lift_coef_mach_table = 0:1