WBcoeffs.ini

[Scorpi1987]

Hi there , currently iam working on the implementiation of the MSFS model in Jeehell

some has the issues that the Weight&Balance calculation is wrong with my Flightmodell.

and the only that ive found what can fix it is the WBcoeffs.ini... but i dont know what the fields mean...

Can somebody explain it for me ?

[Weight&Balance]
LEMAC_FS_ft=3.43963254593
LEMAC_real_m=17.8015
MAC_m=4.1935
MAC_FS_ft=13.7582
DOWarm_FS_ft=-0.26
OAarm_FS_ft=21.397
OBarm_FS_ft=-3.225
OCarm_FS_ft=-26.651
CPT1arm_FS_ft=21.545
CPT3arm_FS_ft=-13.239
CPT4arm_FS_ft=-23.99
CPT5arm_FS_ft=-34.548
OAarm_real_m=12.328
OBarm_real_m=19.832
OCarm_real_m=26.973149
CPT1arm_real_m=12.283
CPT3arm_real_m=22.885
CPT4arm_real_m=26.162
CPT5arm_real_m=29.38
PantryE_real_m=6.6499
PantryF_real_m=33.1499
fixedTKinnerArm_FS_ft=3.31
fixedTKouterArm_FS_ft=-7.60
fixedTKcenterArm_FS_ft=4.15

[jeehell]

Those are used by my soft to compute a CG position from the real acft data.
I then use the CG to update fake weight stations to have the correct CG in P3D.

[Scorpi1987]

ahh that is what i need is it possible to adapt it to my Model Weight and blance ?

[WEIGHT_AND_BALANCE]
max_gross_weight = 174165 ; Empty weight, (LBS)
empty_weight = 90400 ; Empty weight, (LBS)
reference_datum_position = 0, 0, 0 ; Position of reference datum relative to FS(0,0,0) (FEET), z, x, y
empty_weight_CG_position = -9, 0, -1 ; Position of airplane empty weight CG relative to reference datum (FEET), z, x, y
CG_forward_limit = 0.16 ; Gravity center forward limit (longitudinal offset) for longitudinal stability
CG_aft_limit = 0.4 ; Gravity center after limit (longitudinal offset z) w.r.t reference datum for longitudinal stability (FEET)
empty_weight_pitch_MOI = 3027957 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET)
empty_weight_roll_MOI = 840695 ; Empty roll moment of inertia, Jzz (SLUG SQ FEET)
empty_weight_yaw_MOI = 3507948 ; Empty yaw moment of inertia, Jyy (SLUG SQ FEET)
empty_weight_coupled_MOI = 1000 ; 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).
max_number_of_stations = 6 ; Number of payload stations
station_load.0 = 170, 35.59, -1.86, 5.017127, TT:MENU.PAYLOAD.PILOT, 1
station_load.1 = 170, 35.59, 1.86, 5.017127, TT:MENU.PAYLOAD.COPILOT, 2
station_load.2 = 6115, 20.845893, 0, 5.039792, TT:MENU.PAYLOAD.BUSINESS_CLASS, 0
station_load.3 = 3505, 21.825772, 0, 0.94849, TT:MENU.PAYLOAD.FORWARD_BAGGAGE, 0
station_load.4 = 4000, -21.223969, 0, 5.794459, TT:MENU.PAYLOAD.ECONOMY_CLASS, 0
station_load.5 = 6310, -35.825745, 0.000001, 1.007935, TT:MENU.PAYLOAD.REAR_BAGGAGE, 0

[FUEL]
LeftMain = -9, -13, 2, 1800, 0 ; For each tank: Tank position (z longitudinal, x lateral, y vertical) (FEET), total fuel capacity (GALLONS), unusable fuel capacity (GALLONS)
RightMain = -9, 13, 2, 1800, 0
Center1 = -11, 0, 1, 3000, 0
Center2 = 0, 0, 0, 0, 0
Center3 = 0, 0, 0, 0, 0
LeftAux = -13, -27, 3, 200, 0
LeftTip = 0, 0, 0, 0, 0
RightAux = -13, 27, 3, 200, 0
RightTip = 0, 0, 0, 0, 0
External1 = 0, 0, 0, 0, 0
External2 = 0, 0, 0, 0, 0
fuel_type = 2 ; 1 = OCTANE 100, 2 = JET_A, 3 = OCTANE 80, 4 = AUTO GAS, 5 = JET B
number_of_tank_selectors = 1 ; Max 4
electric_pump = 0
engine_driven_pump = 1
manual_transfer_pump = 0
manual_pump = 0
anemometer_pump = 0
fuel_dump_rate = 0.02
default_fuel_tank_selector.1 = 1 ; Default fuel selector used in case of autostart for engine 1, default is ALL.
default_fuel_tank_selector.2 = 1 ; Default fuel selector used in case of autostart for engine 2, default is ALL.
default_fuel_tank_selector.3 = 1 ; Default fuel selector used in case of autostart for engine 3, default is ALL.
default_fuel_tank_selector.4 = 1 ; Default fuel selector used in case of autostart for engine 4, default is ALL.

[Scorpi1987]

[AIRPLANE_GEOMETRY]
wing_area = 1317.5026 ; Wing area S (SQUARE FEET)
wing_span = 117.46 ; Wing span b (FEET)
wing_root_chord = 21 ; Wing root chord croot (FEET)
wing_camber = 1 ; (DEGREES)
wing_thickness_ratio = 0.02 ; Local thickness is local_chord(x)*wing_thickness_ratio, x = lateral coord
wing_dihedral = 7 ; Dihedral angle Lambda (DEGREES)
wing_incidence = 2 ; Wing incidence (DEGREES)
wing_twist = -2 ; Wing twist epsilon (DEGREES)
oswald_efficiency_factor = 0.7388 ; Wing Oswald efficiency factor e (non dimensional)
wing_winglets_flag = 1 ; Has winglets true/false
wing_sweep = 28.76 ; Wing sweep (DEGREES)
wing_pos_apex_lon = 6.193863
wing_pos_apex_vert = -0.1499 ; Vertical (y) position of wing apex w.r.t reference datum (FEET)
htail_area = 363 ; Horizontal tail area (SQUARE FEET)
htail_span = 42.10 ; Horizontal tail span (FEET)
htail_pos_lon = -70.472 ; Longitudinal (z) position of horizontal tail w.r.t reference datum (FEET)
htail_pos_vert = 6.64 ; Vertical (y) position of horizontal tail w.r.t reference datum (FEET)
htail_incidence = 0.27985 ; Horizontal tail incidence (DEGREES)
htail_sweep = 32 ; Horizontal tail sweep angle (DEGREES)
htail_thickness_ratio = 0.02 ; Local thickness is local_chord(x)*htail_thickness_ratio, x = lateral coord
vtail_area = 283.0 ; Vertical tail area (SQUARE FEET)
vtail_span = 19.20 ; Vertical tail span (FEET)
vtail_sweep = 28.00 ; Vertical tail sweep angle (DEGREES)
vtail_pos_lon = -66.436 ; Longitudinal (z) position of vertical tail w.r.t reference datum (FEET)
vtail_pos_vert = 19.70 ; Vertical (y) position of vertical tail w.r.t reference datum (FEET)
vtail_thickness_ratio = 0.028 ; Local thickness is local_chord(x)*vtail_thickness_ratio, x = lateral coord
fuselage_length = 119 ; Nose to tail (FEET)
fuselage_diameter = 14.12
fuselage_center_pos = -7, 0, 5
elevator_area = 151.52 ; Elevator area (SQUARE FEET)
aileron_area = 32.0224 ; Elevator area (SQUARE FEET)
rudder_area = 68.12 ; Rudder area (SQUARE FEET)

[jeehell]

I don't have the time to play with that sorry... it should be possible, you mostly should change the values with "_FS_ft" ending.
if you compare with the aircraft.cfg from my package you should get an idea about it.

[Scorpi1987]

I don't have the time to play with that sorry... it should be possible, you mostly should change the values with "_FS_ft" ending.
if you compare with the aircraft.cfg from my package you should get an idea about it.

Thanks for the tip Ive found out the Values, and modified it with them from MSFS modell.. but i has no effect in CG calculation in MCDU
Ive inserted the original Station.Load points with edited Datum References in the MSFS, thats strange but i dont give up