flight_model.cfg

[VERSION]
major = 1
minor = 0

[WEIGHT_AND_BALANCE]
max_gross_weight = 83500 ; Empty weight, (LBS)
empty_weight = 43340 ; 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 = 12, 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 = 69403 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET)
empty_weight_roll_MOI = 13434 ; Empty roll moment of inertia, Jzz (SLUG SQ FEET)
empty_weight_yaw_MOI = 75997 ; Empty yaw moment of inertia, Jyy (SLUG SQ FEET)
empty_weight_coupled_MOI = 100 ; 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 = 1 ; Number of payload stations
station_load.0 = 170, 27, 0, 6, TT:MENU.PAYLOAD.PILOT, 1

[CONTACT_POINTS]
static_pitch = 10 ; degrees, pitch when at rest on the ground (+=Up, -=Dn)
static_cg_height = 6 ; feet, altitude of CG when at rest on the ground
gear_system_type = 1 ; gear system type (betweeen 0 and 4) 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none, 5 = undefined
tailwheel_lock = 0 ; Is tailwheel lock available TRUE/FALSE
max_number_of_points = 9 ; Number of contact points
gear_locked_on_ground = 0 ; Defines whether or not the landing gear handle is locked to down when the plane is on the ground.
gear_locked_above_speed = -1 ; Defines the speed at which the landing gear handle becomes locked in the up position. (-1 = Disabled)
max_speed_full_steering = 8 ; Defines the speed under which the full angle of steering is available (in feet/second).
max_speed_decreasing_steering = 50 ; Defines the speed above which the angle of steering stops decreasing (in feet/second).
min_available_steering_angle_pct = 0.03 ; 0.2 ; Defines the percentage of steering which will always be available even above max_speed_decreasing_steering (in percent over 100).
max_speed_full_steering_castering = 20 ; Defines the speed under which the full angle of steering is available for free castering wheels (in feet/second).
max_speed_decreasing_steering_castering = 40 ; Defines the speed above which the angle of steering stops decreasing for free castering wheels  (in feet/second).
min_castering_angle = 0.05236 ; Defines the minimum angle a free castering wheel can take (in radians).
max_castering_angle = 3.14159265358979 ; Defines the maximum angle a free castering wheel can take (in radians).
point.0 = 1, 22.5, 0, -2.5, 750, 0, 2, 70, 1, 2.12, 0.33, 2, 2, 0, 400, 600
point.1 = 1, 2.25, -6, -2, 1500, 1, 3, 0, 2, 2.06, 0.33, 2, 2, 2, 400, 600
point.2 = 1, 2.25, 6, -2, 1500, 2, 3, 0, 2, 2.06, 0.33, 2, 2, 3, 400, 600
point.3 = 2, 40, 0, 4, 350, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1
point.4 = 2, 25, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1
point.5 = 2, 0.5, -22, 4, 350, 0, 0, 0, 0, 0, 0, 0, 0, 5, 0, 0, 1
point.6 = 2, 0.5, 22, 4, 350, 0, 0, 0, 0, 0, 0, 0, 0, 6, 0, 0, 1
point.7 = 2, -6, 0, 13.25, 350, 0, 0, 0, 0, 0, 0, 0, 0, 9, 0, 0, 1
point.8 = 2, -17.4, 0, 4, 750, 0, 0, 0, 0, 0, 0, 0, 0, 9, 0, 0, 1

[FUEL]
LeftMain = 12, -1.5, 1.5, 1343, 0 ; For each tank: Tank position (z longitudinal, x lateral, y vertical) (FEET), total fuel capacity (GALLONS), unusable fuel capacity (GALLONS)
RightMain = 12, 1.5, 1.5, 1343, 0
fuel_type = 2 ; 1 = OCTANE 100, 2 = JET_A, 3 = OCTANE 80, 4 = AUTO GAS, 5 = JET B
number_of_tank_selectors = 2 ; Max 4
electric_pump = 1
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.
fuel_transfer_pump.0 = 19, 20, 0.0714, 1
fuel_transfer_pump.1 = 20, 19, 0.0714, 2

[AIRPLANE_GEOMETRY]
wing_area = 1450 ; Wing area S (SQUARE FEET)
wing_span = 44 ; Wing span b (FEET)
wing_root_chord = 62 ; Wing root chord croot (FEET) 60 is right
wing_camber = 0 ; (DEGREES)
wing_thickness_ratio = 0.008 ; Local thickness is local_chord(x)*wing_thickness_ratio, x = lateral coord
wing_dihedral = -1.5 ; Dihedral angle Lambda (DEGREES)
wing_incidence = 0 ; Wing incidence (DEGREES)
wing_twist = 0 ; Wing twist epsilon (DEGREES)
oswald_efficiency_factor = 0.9 ; Wing Oswald efficiency factor e (non dimensional)
wing_winglets_flag = 0 ; Has winglets true/false
wing_sweep = 41 ; Wing sweep (DEGREES) 45 is right
; wing_pos_apex_lon = -1 ; Longitudinal (z) position of wing apex w.r.t reference datum (FEET) was 5.51747
wing_pos_apex_vert = 4 ; Vertical (y) position of wing apex w.r.t reference datum (FEET) 4 is right
htail_area = 200 ; Horizontal tail area (SQUARE FEET)
htail_span = 28 ; Horizontal tail span (FEET)
htail_pos_lon = -13 ; Longitudinal (z) position of horizontal tail  w.r.t reference datum (FEET)
htail_pos_vert = 3.7 ; Vertical (y) position of horizontal tail  w.r.t reference datum (FEET)
htail_incidence = 0 ; Horizontal tail incidence (DEGREES)
htail_sweep = 41 ; Horizontal tail sweep angle (DEGREES)
htail_thickness_ratio = 0.002 ; Local thickness is local_chord(x)*htail_thickness_ratio, x = lateral coord
vtail_area = 100 ; Vertical tail area (SQUARE FEET)
vtail_span = 10 ; Vertical tail span (FEET)
vtail_sweep = 45 ; Vertical tail sweep angle (DEGREES)
vtail_pos_lon = 0.1 ; Longitudinal (z) position of vertical tail  w.r.t reference datum (FEET)
vtail_pos_vert = 8 ; Vertical (y) position of vertical tail  w.r.t reference datum (FEET)
vtail_thickness_ratio = 0.002 ; Local thickness is local_chord(x)*vtail_thickness_ratio, x = lateral coord
fuselage_length = 55 ; Nose to tail (FEET)
fuselage_diameter = 4
fuselage_center_pos = 15, 0, 3.75
elevator_area = 500 ; Elevator area (SQUARE FEET)
aileron_area = 200 ; Elevator area (SQUARE FEET)
rudder_area = 200 ; Elevator area (SQUARE FEET)
elevator_up_limit = 45 ; Elevator max deflection up angle (DEGREES)
elevator_down_limit = 30 ; Elevator max deflection down angle (absolute value) (DEGREES)
aileron_up_limit = 40 ; Aileron max deflection  angle (DEGREES)
aileron_down_limit = 30 ; Aileron max deflection down angle (absolute value) (DEGREES)
rudder_limit = 22 ; Rudder max deflection angle (absolute value) (DEGREES)
rudder_trim_limit = 16 ; Rudder trim max deflection angle (absolute value) (DEGREES)
elevator_trim_limit = 50 ; Elevator trim max angle (absolute value) (DEGREES)
spoiler_limit = 60 ; Spoiler max deflection angle (absolute value) (DEGREES)
spoilerons_available = 0 ; Aircraft has spoilerons true/false
aileron_to_spoileron_gain = 4.6 ; Aileron influence on spoileron angle (non-dimensional)
min_ailerons_for_spoilerons = 5 ; Minimum aileron deflection (absolute value) in which spoilerons are active (DEGREES)
min_flaps_for_spoilerons = 0 ; Minimum flaps deflection (absolute value) in which spoilerons are active (DEGREES)
spoiler_extension_time = 2 ; Spoilers extension time (SECONDS)
spoiler_handle_available = 1 ; Spoiler handles available true/false
auto_spoiler_available = 0 ; Auto spoilers available true/false
auto_spoiler_min_speed = 0 ; Auto spoilers minimum trigger speed
positive_g_limit_flaps_up = 12 ; Flap positive load limit when up. Same dimension as gravity vector FEET/SECONDS^2
positive_g_limit_flaps_down = 7.1 ; Flap positive load limit when down. Same dimension as gravity vector FEET/SECONDS^2
negative_g_limit_flaps_up = -11 ; Flap negative load limit when up. Same dimension as gravity vector FEET/SECONDS^2
negative_g_limit_flaps_down = -6.7 ; Flap negative load limit when down. Same dimension as gravity vector FEET/SECONDS^2
load_safety_factor = 1 ; Flap negative load limit when down. Same dimension as gravity vector FEET/SECONDS^2
elevator_trim_neutral = 4 ; Elevator trim max angle (absolute value) (DEGREES), for indicators only (no influence on flight model)
aileron_to_rudder_scale = 0 ; non-dimensional
flap_to_aileron_scale = 0 ; non-dimensional
fly_by_wire = 0 ; Fly-by-wire available true/false
elevator_elasticity_table = 0:1, 45:1, 200:0.33, 450:0.25
aileron_elasticity_table = 0:1, 45:1, 200:0.33, 450:0.25
rudder_elasticity_table = 0:1, 45:1, 200:0.33, 450:0.25
elevator_trim_elasticity_table = 0:1, 45:1, 200:0.33, 450:0.25

[AERODYNAMICS]
lift_coef_pitch_rate = -23.65724 ; 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 = -1.07922 ; 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 = 0.5018 ; Change in lift due to flaps
lift_coef_spoilers = -0.1 ; Change in lift due to spoilers
drag_coef_zero_lift = 0.00227 ; 0.0227 ; The zero lift drag polar
drag_coef_flaps = 0.1453
drag_coef_gear = 0.005 ; 0.005
drag_coef_spoilers = 0.1
side_force_slip_angle = -2.74637 ; (yaw angle) The change in side force per change in side slip angle
side_force_roll_rate = 0.56854 ; (roll velocity)  The change in side force per change in roll rate
side_force_yaw_rate = 2.84314 ; (yaw velocity) The change in side force per change in yaw rate
side_force_delta_rudder = -2.54923 ; The change in side force per change in rudder deflection
pitch_moment_horizontal_incidence = 0 ; The change in pitch moment per change in horizontal incidence angle
pitch_moment_delta_elevator = -3.97964 ; The change in pitch moment per change in elevator deflection
pitch_moment_delta_trim = -3.97964 ; The change in pitch moment per change in trim
pitch_moment_pitch_damping = -419.7973 ; The change in pitch moment per change in pitch rate(PRIMARY PITCH STABILITY FACTOR). deg/s
pitch_moment_aoa_0 = -0.15332 ; Pitch moment at zero angle - of - attack
pitch_moment_daoa = 0 ; The change in pitch moment per change in angle of attack
pitch_moment_flaps = -0.05213 ; The pitch moment due to flaps
pitch_moment_gear = 0.00306 ; The pitch moment due to gear
pitch_moment_spoilers = -0.0193 ; The pitch moment due to spoilers
pitch_moment_delta_elevator_propwash = -0.99491
pitch_moment_pitch_propwash = 0
roll_moment_slip_angle = 0.24939 ; The change in roll moment per sideslip angle(DIHEDRAL EFFECT)
roll_moment_roll_damping = -1.4369
roll_moment_yaw_rate = -0.24061
roll_moment_spoilers = 0 ; The change in roll moment due to spoilers
roll_moment_delta_aileron = -0.15163 ; (control)The change in roll moment per change in aileron deflection
roll_moment_delta_rudder = 0.33028 ; (control)The change in roll moment per change rudder deflection
roll_moment_delta_aileron_trim_scalar = -0.15163 ; Change in roll moment due to aileron trim
yaw_moment_slip_angle = 0.89291 ; The change in yaw moment per change sideslip angle(WEATHER VANING EFFECT)
yaw_moment_roll = 0.08554 ; (adverse yaw) The change in yaw moment per change in roll rate deg/s
yaw_moment_yaw_damping = -6.85431 ; (damping)The change in yaw moment per change in yaw rate(PRIMARY YAW STABILITY FACTOR deg/s)
yaw_moment_yaw_propwash = 0 ; (damping)
yaw_moment_delta_aileron = 0.00382 ; (adverse yaw)  The change in yaw moment per change aileron deflection
yaw_moment_delta_rudder = 1.1374 ; (control)The change in yaw moment per change in rudder deflection PRIMARY YAW POWER FACTOR
yaw_moment_delta_rudder_propwash = 0.28435 ; (control)
yaw_moment_delta_rudder_trim_scalar = 1.1374 ; Change in yaw moment due to rudder trim
compute_aero_center = 0
aero_center_lift = 1 ; Init to center
lift_coef_aoa_table = -3.15:0, -0.8:-1.185, -0.4:-0.987, -0.2:-0.698, -0.1:-0.489, 0:0.038, 0.2:1.154, 0.23:1.279, 0.26:1.39, 0.29:1.249, 0.31:1.159, 0.4:1.031, 0.8:1.207, 3.15:0
lift_coef_ground_effect_mach_table = 0.054:1.25
lift_coef_mach_table = 0:1
lift_coef_delta_elevator_mach_table = 0:0
lift_coef_daoa_mach_table = 0:0
lift_coef_pitch_rate_mach_table = 0:0
lift_coef_horizontal_incidence_mach_table = 0:0
drag_coef_zero_lift_mach_tab = 0:0, 0.5:0, 0.55:0, 0.6:0, 0.65:0, 0.7:0, 0.75:0, 0.8:0, 0.85:0, 0.9:0, 0.95:0, 1:0, 1.1:0, 1.5:0, 1.55:0, 1.6:0, 1.65:0, 1.7:0, 1.75:0, 1.8:0, 1.85:0, 1.9:0, 1.95:0.3
                             ; 0:0, 0.5:0, 0.55:0, 0.6:0, 0.65:0, 0.7:0, 0.75:0, 0.8:0, 0.85:0, 0.9:0, 0.95:0, 1:2, 1.1:2, 1.5:2
side_force_slip_angle_mach_table = 0:0
side_force_delta_rudder_mach_table = 0:0
side_force_yaw_rate_mach_table = 0:0
side_force_roll_rate_mach_table = 0:0
pitch_moment_aoa_table = -3.15:0, -0.8:-1.599, -0.4:-1.272, -0.2:-0.686, -0.1:-0.348, 0:0, 0.2:0.742, 0.23:0.834, 0.26:0.92, 0.29:1.117, 0.31:1.224, 0.4:1.508, 0.8:1.962, 3.15:0
pitch_moment_delta_elevator_aoa_table = -180:-1, -40:0.183, -20:0.697, -10:0.993, -5:1.091, 0:1, 5:0.815, 10:0.633, 20:0.298, 40:-0.164, 180:-1 ; AoA(alpha) is given in DEGREES
pitch_moment_horizontal_incidence_aoa_table = 0:1 ; AoA(alpha) is given in DEGREES
pitch_moment_daoa_aoa_table = 0:1 ; AoA(alpha) is given in DEGREES
pitch_moment_pitch_alpha_table = 0:1 ; AoA(alpha) is given in DEGREES
pitch_moment_delta_elevator_mach_table = 0:0
pitch_moment_daoa_mach_table = 0:0
pitch_moment_pitch_rate_mach_table = 0:0
pitch_moment_horizontal_incidence_mach_table = 0:0
pitch_moment_aoa_0_mach_table = 0:0
roll_moment_aoa_table = 0:0 ; Cl (roll moment coef) versus AoA
roll_moment_slip_angle_aoa_table = 0:1
roll_moment_roll_rate_aoa_table = 0:1
roll_moment_delta_aileron_aoa_table = 0:1
roll_moment_slip_angle_mach_table = 0:0
roll_moment_delta_rudder_mach_table = 0:0
roll_moment_delta_aileron_mach_table = 0:0
roll_moment_yaw_rate_mach_table = 0:0
roll_moment_roll_rate_mach_table = 0:0
yaw_moment_aoa_table = 0:0 ; Cn (yaw moment coef) versus AoA
yaw_moment_slip_angle_aoa_table = 0:1
yaw_moment_yaw_rate_aoa_table = 0:1
yaw_moment_delta_rudder_aoa_table = 0:1
yaw_moment_slip_angle_mach_table = 0:0
yaw_moment_delta_rudder_mach_table = 0:0
yaw_moment_delta_aileron_mach_table = 0:0
yaw_moment_yaw_rate_mach_table = 0:0
yaw_moment_roll_rate_mach_table = 0:0
elevator_scaling_table = 0:1 ; scales control based on its deflection
aileron_scaling_table = 0:1 ; scales control based on its deflection
rudder_scaling_table = 0:1 ; scales control based on its deflection
aileron_load_factor_effectiveness_table = 0:1 ; scaling of roll_moment_delta_aileron versus gravity forces, G effects on aileron effectiveness, acts on roll_moment_delta_aileron
lift_coef_at_drag_zero = 0.10000
lift_coef_at_drag_zero_flaps = 0.10000

[FLIGHT_TUNING]
cruise_lift_scalar = 1
parasite_drag_scalar = 1
induced_drag_scalar = 1
flap_induced_drag_scalar = 1
elevator_effectiveness = 1
elevator_maxangle_scalar = 1
aileron_effectiveness = 1
rudder_effectiveness = 1
rudder_maxangle_scalar = 1
pitch_stability = 1
roll_stability = 1
yaw_stability = 1
elevator_trim_effectiveness = 1
aileron_trim_effectiveness = 1
rudder_trim_effectiveness = 1
hi_alpha_on_roll = 0
hi_alpha_on_yaw = 0
p_factor_on_yaw = 0
torque_on_roll = 0
gyro_precession_on_roll = 0
gyro_precession_on_yaw = 0
engine_wash_on_roll = 0 ; Torque effect
wingflex_scalar = 0.5 ; 1
wingflex_offset = 0

[REFERENCE SPEEDS]
full_flaps_stall_speed = 90 ; Knots True (KTAS)
flaps_up_stall_speed = 105 ; Knots True (KTAS)
cruise_speed = 1267 ; Knots True (KTAS)
cruise_mach = 1.96
crossover_speed = 285 ; Knots Indicated (KIAS)
max_mach = 2.42
max_indicated_speed = 1614 ; Red line (KIAS)
max_flaps_extended = 900
normal_operating_speed = 1600
airspeed_indicator_max = 1700
rotation_speed_min = 115 ; Min speed required (Kts)
climb_speed = 138 ; Climb speed (Kts)
cruise_alt = 60000 ; (ft)
takeoff_speed = 135 ; Takeoff Speed (Kts)
spawn_cruise_altitude = 40000 ; Spawn Cruise Altitude (ft)
spawn_descent_altitude = 500 ; Spawn Descent Altitude (ft)
best_angle_climb_speed = 0 ; Best angle climb speed (Kts)
approach_speed = 110 ; Approach speed (Kts)
best_glide = 1100 ; Best Glide (Kts)

[INTERACTIVE POINTS]
number_of_interactive_points = 0

;===================== FLAPS =====================

[FLAPS.0]
type = 1 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge
system_type = 1 ; Flap system type 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none
span-outboard = 0.57 ; Outboard span area (added area) (percentage, non dimensional)
extending-time = 1 ; Flap extension time (SECONDS)
damaging-speed = 500 ; Speed above which flap is damaged (Kts)
blowout-speed = 600 ; Speed above which flap is blown out (Kts)
maneuvering_flaps = 0
lift_scalar = 1.6 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
drag_scalar = 1.6 ; 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 = 2 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found.
flaps-position.0 = 0, -1, 0, 0, 0, 0, 0
flaps-position.1 = 15, -1, 0.5, 0, 0, 0, 0
flaps-position.2 = 35, -1, 1, 0, 0, 0, 0