;-----------------------------------------------------------------------------------------------------
: Canso PBY-5A - FrenchVFR (c) 2010-2021
;-----------------------------------------------------------------------------------------------------
[VERSION]
major =1
minor =0
[WEIGHT_AND_BALANCE]
max_gross_weight =35420
empty_weight =17837
reference_datum_position = 0, 0, 0
empty_weight_cg_position = 1.472693, 0, 2.026568
cg_forward_limit =0
cg_aft_limit =0.3
empty_weight_pitch_moi =152434.56
empty_weight_roll_moi =103168.44
empty_weight_yaw_moi =202947.07
empty_weight_coupled_moi =0
max_number_of_stations =6
station_load.0=720, 12, 0, 3.2, Equipage, 0
station_load.1=160, 8.6, 0, 2.7, Navigator, 0
station_load.2=3300, 1.5, -2.5, -1.2, Tanker #1, 0
station_load.3=3300, 1.5, 2.5, -1.2, Tanker #2, 0
station_load.4= 100, -15.0, -2.0, 3.0, Cargo #1, 0
station_load.5= 100, -15.0, 2.0, 3.0, Cargo #2, 0
activate_mach_limit_based_on_cg =0
activate_cg_limit_based_on_mach =0
[FLIGHT_TUNING]
cruise_lift_scalar =1
parasite_drag_scalar =1
induced_drag_scalar =1
elevator_effectiveness =1
aileron_effectiveness =1
rudder_effectiveness =1
pitch_stability =1
roll_stability =1
yaw_stability =1
elevator_trim_effectiveness =0.8
aileron_trim_effectiveness =0.8
rudder_trim_effectiveness =0.8
hi_alpha_on_roll =1
hi_alpha_on_yaw =1
p_factor_on_yaw =1
torque_on_roll =1
gyro_precession_on_roll = 1
gyro_precession_on_yaw =1
stall_coef_at_min_weight =0.5
flap_induced_drag_scalar =1
wingflex_scalar =1
wingflex_offset =0
predicted_moi_density_scalar_fuselage =1
predicted_moi_density_scalar_wings =1
elevator_maxangle_scalar =1
elevator_chordangle_scalar =-1
htail_maxangle_scalar =-1
rudder_maxangle_scalar =1
rudder_chordangle_scalar =-1
vtail_maxangle_scalar=-1
pitch_gyro_stability=0
roll_gyro_stability=0
yaw_gyro_stability=0
engine_wash_on_roll=0
rudder_engine_wash_on_roll=1
gyro_precession_on_pitch=1
elevator_maxangle_scalar = 1 ;
rudder_maxangle_scalar = 1 ;
engine_wash_on_roll = 0 ; Torque effect
wingflex_scalar = 0.3 ;
wingflex_offset = 0.0 ;
empty_CG_deviation_limit=10000
icing_scalar=1
modern_fm_only=0
[FUEL]
; For each tank: Tank position (z longitudinal, x lateral, y vertical) (FEET), total fuel capacity (GALLONS), unusable fuel capacity (GALLONS)
leftmain = -1.15, -19.1, 9.64726, 875, 5
rightmain = -1.15, 19.1, 9.647, 875, 5
; 1 = OCTANE 100, 2 = JET_A, 3 = OCTANE 80, 4 = AUTO GAS, 5 = JET B
fuel_type =1
number_of_tank_selectors =2
electric_pump =1
fuel_dump_rate =0.01
engine_driven_pump =1
manual_transfer_pump =0
manual_pump =0
anemometer_pump =0
default_fuel_tank_selector.1 =1
default_fuel_tank_selector.2 =1
default_fuel_tank_selector.3 =1
default_fuel_tank_selector.4 =1
[CONTACT_POINTS]
; 0 Class
; 1 Longitudinal Position (feet)
; 2 Lateral Position (feet)
; 3 Vertical Position (feet)
; 4 Impact Damage Threshold (Feet Per Minute)
; 5 Brake Map (0=None, 1=Left, 2=Right)
; 6 Wheel Radius (feet)
; 7 Steer Angle (degrees)
; 8 Static Compression (feet) (0 if rigid)
; 9 Max/Static Compression Ratio
; 10 Damping Ratio (0=Undamped, 1=Critically Damped)
; 11 Extension Time (seconds)
; 12 Retraction Time (seconds)
; 13 Sound Type
; 14 Airspeed limit for retraction (KIAS)
; 15 Airspeed that gear gets damage at (KIAS)
static_pitch =1.2
static_cg_height =4.30
gear_system_type =1
max_number_of_points =16
; /Gears
point.0 = 1, 14.999941, 0, -5.5, 2300, 0, 0.39, 40, 0.5, 3, 0.99, 4, 10, 0, 123.2, 140.8, 1
point.1 = 1, -1.85, -8.4, -5.1, 2500, 1, 1.85, 0, 0.259, 2.35, 0.95, 5.5, 10, 2, 123.2, 140.8, 1
point.2 = 1, -1.85, 8.4, -5.1, 2500, 2, 1.85, 0, 0.259, 2.35, 0.95, 6, 11, 3, 123.2, 140.8, 1
; /Scrapes
point.3 = 2, 19.5, 0, -1, 2500, 0, 0, 0, 0, 0, 1, 0, 0, 4, 0, 0, 1
point.4 = 2, -42.6, 0, 4.8, 2500, 0, 0, 0, 0, 0, 1, 0, 0, 4, 0, 0, 1
point.5 = 2, -37, 0, 3.6, 2500, 0, 0, 0, 0, 0, 1, 0, 0, 4, 0, 0, 1
point.6 = 2, -1.25, -52, 8.75, 2500, 0, 0, 0, 0, 0, 1, 0, 0, 4, 0, 0, 1
point.7 = 2, -1.25, 52, 8.75, 2500, 0, 0, 0, 0, 0, 1, 0, 0, 4, 0, 0, 1
point.8 = 2, 10.2, 0, 7.1618, 2500, 0, 0, 0, 0, 0, 1, 0, 0, 4, 0, 0, 1
; /Wing Floats
point.9 = 4, 14, 0, -1, 500, 0, 0, 0, 0.25, 1, 0.5, 0, 0, 5, 0, 0, 1 // Front Float
point.10 = 4, -2, -6.2, -0.82, 2500, 0, 0, 0, 0.25, 1, 0.5, 0, 0, 5, 0, 0, 1 // Left Gear Float Line
point.11 = 4, -2, 6.2, -0.82, 2500, 0, 0, 0, 0.25, 1, 0.5, 0, 0, 5, 0, 0, 1 // Right Gear Float Line
point.12 = 4, -1, -45.3, 1.27, 1500, 0, 0, 0, 0.5, 2.5, 0.7, 12, 11, 5, 0, 0, 1 // Left Wing Float
point.13 = 4, -1, 45.3, 1.27, 1500, 0, 0, 0, 0.5, 2.5, 0.7, 14, 11, 5, 0, 0, 1 // Right Wing Float
; /Water Rudders
point.14 = 4, -20.3, -3.5, -0.82, 1600, 0, 0, 15, 0, 0, 0.1, 1, 1.5, 0, 0, 0, 1 // Left Rudder Location
point.15 = 4, -20.3, 3.5, -0.82, 1600, 0, 0, 15, 0, 0, 0.1, 1, 1.5, 0, 0, 0, 1 // Right Rudder Location
tailwheel_lock =0
max_speed_full_steering =120
max_speed_decreasing_steering = 120 ; Old value 20 - Defines the speed above which the angle of steering stops decreasing (in feet/second).emergency_extension_type =1
gear_locked_on_ground =0
gear_locked_above_speed =-1
steering_time_constants = 3, 5
hyd_need_power_to_function=0
emergency_extension_type=1
[AIRPLANE_GEOMETRY]
wing_area =1400
wing_span =104
wing_root_chord =15
wing_dihedral =2.33
wing_incidence =10
wing_twist =0
oswald_efficiency_factor =0.957
wing_winglets_flag =0
wing_sweep =2.97
wing_pos_apex_lon =3.87929
wing_pos_apex_vert =6.56
htail_area =138.2
htail_span =30.5
htail_pos_lon =-30.8
htail_pos_vert =9.06
htail_incidence =4
htail_sweep =10.88
vtail_area =108.8
vtail_span =10.6
vtail_sweep =52
vtail_pos_lon =-27.1
vtail_pos_vert =4.06
elevator_area =66.6
aileron_area =100
rudder_area =40.4
elevator_up_limit =30
elevator_down_limit =20
aileron_up_limit =21
aileron_down_limit =19.75
rudder_limit =17
elevator_trim_limit = 8
aileron_to_spoileron_gain =0
min_ailerons_for_spoilerons =0
min_flaps_for_spoilerons =0
auto_spoiler_available =0
load_safety_factor =1.6
wing_camber =1
wing_thickness_ratio =0.02
htail_thickness_ration = 0.02
vtail_thickness_ratio =0.02
fuselage_center_pos = 5.73, 0, -0.4
rudder_trim_limit =20
spoiler_handle_available =1
auto_spoiler_min_speed =0
elevator_trim_neutral =0
aileron_to_rudder_scale =0
flap_to_aileron_scale =0
fly_by_wire =0
fuselage_length = 83.2
fuselage_diameter =3.8
;===========================
elevator_elasticity_table =0.000000:1.000000, 114.314766:1.000000, 212.078687:0.660000, 414.920262:0.330000, 1344.341647:0.100000
aileron_elasticity_table =0.000000:1.000000, 114.314766:1.000000, 212.078687:0.660000, 414.920262:0.330000, 1344.341647:0.100000
rudder_elasticity_table =0.000000:1.000000, 114.314766:1.000000, 212.078687:0.660000, 414.920262:0.330000, 1344.341647:0.100000
elevator_trim_elasticity_table =0.000000:1.000000, 114.314766:1.000000, 212.078687:0.660000, 414.920262:0.330000, 1344.341647:0.100000
auto_spoiler_auto_retracts =1
htail_thickness_ratio=0.1
spoiler_limit=0
air_spoiler_limit=0
spoilerons_available=0
spoiler_extension_time=0
spoiler_disabled_by_flaps=0
positive_g_limit_flaps_up=4
positive_g_limit_flaps_down=2
negative_g_limit_flaps_up=-1.5
negative_g_limit_flaps_down=-1.5
[REFERENCE SPEEDS]
;-A verifier
;==========================
flaps_up_stall_speed =59
full_flaps_stall_speed =59
cruise_speed =137
max_indicated_speed =190
max_mach =0.301
rotation_speed_min =-0.592398
climb_speed =-0.592398
cruise_alt =1500
takeoff_speed =55
max_flaps_extended =62.656664
normal_operating_speed =152
airspeed_indicator_max =237.5
spawn_cruise_altitude =1500
spawn_descent_altitude =500
best_angle_climb_speed =0
approach_speed =129.473865
best_glide =0
max_gear_extended =320.73056
cruise_mach =0.301
crossover_speed =256.584442
normal_operating_speed = 360
fly_assistant_use_dynamic_speeds=0
;===========================
[AERODYNAMICS]
lift_coef_pitch_rate =-3.466797
lift_coef_daoa =1.583672
lift_coef_delta_elevator =-0.073242
lift_coef_horizontal_incidence =1.4006
lift_coef_flaps =0.1600
lift_coef_spoilers =-0.0700
drag_coef_zero_lift =0.0388
drag_coef_flaps =0.1221
drag_coef_gear =0.0566
drag_coef_spoilers =0.4883
side_force_slip_angle =-0.3936
side_force_roll_rate =0.0327
side_force_yaw_rate =0.2207
side_force_delta_rudder =-0.0928
pitch_moment_horizontal_incidence =0.24414
pitch_moment_delta_elevator =-4.1016
pitch_moment_delta_trim =-8.000
pitch_moment_pitch_damping =-31.7383
pitch_moment_aoa_0 =-0.42968
pitch_moment_daoa =2.92968
pitch_moment_flaps =0.000
pitch_moment_gear =0.0171
pitch_moment_spoilers =0.4850
pitch_moment_delta_elevator_propwash =-0.0100
pitch_moment_pitch_propwash =0
roll_moment_slip_angle =0.03710
roll_moment_roll_damping =-1.20117
roll_moment_yaw_rate =-0.11718
roll_moment_spoilers =0.0000
roll_moment_delta_aileron =-0.46337
roll_moment_delta_rudder =-0.01806
roll_moment_delta_aileron_trim_scalar =-0.005236
yaw_moment_slip_angle =0.42968
yaw_moment_roll =-0.02929
yaw_moment_yaw_damping =-0.10253
yaw_moment_yaw_propwash =0
yaw_moment_delta_aileron =-1.05468
yaw_moment_delta_rudder =0.64599
yaw_moment_delta_rudder_propwash =0
yaw_moment_delta_rudder_trim_scalar =0.005236
compute_aero_center =1
aero_center_lift =-0.8
lift_coef_aoa_table =-3.141593:0.000000, -2.844294:0.935946, -2.809387:0.837426, -1.727876:0.669941, -0.350000:-1.220000, 0.000000:0.200000, 0.261800:1.531100, 0.314752:1.175553, 0.332206:1.019612, 1.413717:0.815690, 1.727876:-0.669941, 2.809387:-0.837426, 2.844294:-0.935946, 3.141593:0.000000
lift_coef_ground_effect_mach_table =0.054000:1.250000, 0.100000:1.160000, 0.200000:1.096100, 0.300000:1.060000, 0.400000:1.040000, 0.500000:1.030000, 0.600000:1.024200, 0.700000:1.021300, 0.800000:1.016100, 0.900000:1.010000, 1.000000:1.000000
lift_coef_mach_table =0.000000:1.000000, 0.200000:1.000000, 0.400000:1.000000, 0.600000:1.000000, 0.800000:1.000000, 1.000000:1.000000, 1.200000:1.000000, 1.400000:1.000000, 1.600000:1.000000, 1.800000:1.000000, 2.000000:1.000000, 2.200000:1.000000, 2.400000:1.000000, 2.600000:1.000000, 2.800000:1.000000, 3.000000:1.000000, 3.200000:1.000000
lift_coef_delta_elevator_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
lift_coef_daoa_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
lift_coef_pitch_rate_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
lift_coef_horizontal_incidence_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
drag_coef_zero_lift_mach_tab =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.810000:0.000000, 0.820000:0.030000, 0.850000:0.100000, 1.000000:0.200000, 1.200000:0.100000
side_force_slip_angle_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
side_force_delta_rudder_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
side_force_yaw_rate_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
side_force_roll_rate_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
pitch_moment_aoa_table =-3.141593:0.000000, -1.570796:-1.082005, -0.594598:-1.082005, -0.297299:-0.270501, 0.000000:0.000000, 0.297299:0.270501, 0.594598:1.082005, 1.570796:1.082005, 3.141593:0.000000
pitch_moment_delta_elevator_aoa_table =-23.460677:0.700000, -17.773240:0.952272, 0.000000:1.000000, 17.033986:0.956131, 22.484862:0.700000
pitch_moment_horizontal_incidence_aoa_table =-19.550564:0.942347, -17.328909:0.954611, 0.000000:1.000000, 16.608137:0.958282, 18.737385:0.947001
pitch_moment_daoa_aoa_table =-23.460677:0.917334, -17.773240:0.952272, 0.000000:1.000000, 17.033986:0.956131, 22.484862:0.923981
pitch_moment_pitch_alpha_table =-17.773240:0.952272, 0.000000:1.000000, 17.033986:0.956131, 17.459836:0.300000, 22.484862:0.100000
pitch_moment_delta_elevator_mach_table =0.000000:0.000000, 0.200000:0.024426, 0.400000:0.049340, 0.600000:0.073766, 0.800000:0.098681, 1.000000:0.123596, 1.200000:0.123596, 1.400000:0.123596, 1.600000:0.123596, 1.800000:0.123596, 2.000000:0.123596, 2.200000:0.123596, 2.400000:0.123596, 2.600000:0.123596, 2.800000:0.123596, 3.000000:0.123596, 3.200000:0.123596
pitch_moment_daoa_mach_table =0.000000:0.000000, 0.200000:0.244260, 0.400000:0.977040, 0.600000:3.419638, 0.800000:7.816317, 1.000000:7.816317, 1.200000:7.816317, 1.400000:7.816317, 1.600000:7.816317, 1.800000:7.816317, 2.000000:7.816317, 2.200000:7.816317, 2.400000:7.816317, 2.600000:7.816317, 2.800000:7.816317, 3.000000:7.816317, 3.200000:7.816317
pitch_moment_pitch_rate_mach_table =0.000000:0.000000, 0.200000:-0.488520, 0.400000:-1.367855, 0.600000:-2.540303, 0.800000:-3.908158, 1.000000:-4.689790, 1.200000:-4.885198, 1.400000:-4.885198, 1.600000:-4.885198, 1.800000:-4.885198, 2.000000:-4.885198, 2.200000:-4.885198, 2.400000:-4.885198, 2.600000:-4.885198, 2.800000:-4.885198, 3.000000:-4.885198, 3.200000:-4.885198
pitch_moment_horizontal_incidence_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
pitch_moment_aoa_0_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
roll_moment_aoa_table =-22.216550:0.000000, -17.773240:0.000000, 0.000000:0.000000, 11.923790:0.000000, 16.912774:0.000000, 18.124895:0.000000, 20.390507:0.000000
roll_moment_slip_angle_aoa_table =-180.000000:1.000000, -75.000000:0.258819, -18.661902:0.947423, -18.217571:0.949876, 0.000000:1.000000, 17.459836:0.953928, 17.885686:0.951671, 75.000000:0.258819, 180.000000:1.000000
roll_moment_roll_rate_aoa_table =-180.000000:1.000000, -75.000000:0.258819, -18.661902:0.947423, -18.217571:0.949876, 0.000000:1.000000, 17.459836:0.953928, 17.885686:0.951671, 75.000000:0.258819, 180.000000:1.000000
roll_moment_delta_aileron_aoa_table =-19.550564:0.166937, -18.217571:0.667749, 0.000000:1.000000, 17.459836:0.667749, 18.737385:0.166937
roll_moment_slip_angle_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
roll_moment_delta_rudder_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
roll_moment_delta_aileron_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
roll_moment_yaw_rate_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
roll_moment_roll_rate_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:-0.045921, 1.000000:-0.114802, 1.200000:-0.230093, 1.400000:-0.344895, 1.600000:-0.460186, 1.800000:-0.460186, 2.000000:-0.460186, 2.200000:-0.460186, 2.400000:-0.460186, 2.600000:-0.460186, 2.800000:-0.460186, 3.000000:-0.460186, 3.200000:-0.460186
yaw_moment_aoa_table =-22.216550:0.000000, -17.773240:0.000000, 0.000000:0.000000, 11.923790:0.000000, 16.912774:0.000000, 18.124895:0.000000, 20.390507:0.000000
yaw_moment_slip_angle_aoa_table =-180.000000:0.949876, -90.000000:0.500000, -23.460677:0.917334, -18.217571:0.949876, 0.000000:1.000000, 17.459836:0.953928, 22.484862:0.923981, 90.000000:0.500000, 180.000000:0.953928
yaw_moment_yaw_rate_aoa_table =-180.000000:0.949876, -90.000000:0.500000, -23.460677:0.917334, -18.217571:0.949876, 0.000000:1.000000, 17.459836:0.953928, 22.484862:0.923981, 90.000000:0.500000, 180.000000:0.953928
yaw_moment_delta_rudder_aoa_table =-90.000000:0.300000, -17.328909:0.954611, 0.000000:1.000000, 16.608137:0.958282, 90.000000:0.300000
yaw_moment_slip_angle_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
yaw_moment_delta_rudder_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:-0.003908, 0.600000:-0.008305, 0.800000:-0.012702, 1.000000:-0.012702, 1.200000:-0.012702, 1.400000:-0.012702, 1.600000:-0.012702, 1.800000:-0.012702, 2.000000:-0.012702, 2.200000:-0.012702, 2.400000:-0.012702, 2.600000:-0.012702, 2.800000:-0.012702, 3.000000:-0.012702, 3.200000:-0.012702
yaw_moment_delta_aileron_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
yaw_moment_yaw_rate_mach_table =0.000000:0.000000, 0.200000:-0.510992, 0.400000:-1.022472, 0.600000:-1.533952, 0.800000:-2.045432, 1.000000:-2.045432, 1.200000:-2.045432, 1.400000:-2.045432, 1.600000:-2.045432, 1.800000:-2.045432, 2.000000:-2.045432, 2.200000:-2.045432, 2.400000:-2.045432, 2.600000:-2.045432, 2.800000:-2.045432, 3.000000:-2.045432, 3.200000:-2.045432
yaw_moment_roll_rate_mach_table =0.000000:0.000000, 0.200000:0.000000, 0.400000:0.000000, 0.600000:0.000000, 0.800000:0.000000, 1.000000:0.000000, 1.200000:0.000000, 1.400000:0.000000, 1.600000:0.000000, 1.800000:0.000000, 2.000000:0.000000, 2.200000:0.000000, 2.400000:0.000000, 2.600000:0.000000, 2.800000:0.000000, 3.000000:0.000000, 3.200000:0.000000
elevator_scaling_table =-0.349066:1.000000, -0.232711:1.000000, -0.116355:1.000000, 0.000000:1.000000, 0.162897:1.000000, 0.325795:1.000000, 0.488692:1.000000
aileron_scaling_table =-0.453786:1.000000, -0.302524:1.000000, -0.151262:1.000000, 0.000000:1.000000, 0.151262:1.000000, 0.302524:1.000000, 0.453786:1.000000
rudder_scaling_table =-0.436332:1.000000, -0.290888:1.000000, -0.145444:1.000000, 0.000000:1.000000, 0.145444:1.000000, 0.290888:1.000000, 0.436332:1.000000
aileron_load_factor_effectiveness_table =0.000000:1.000000, 2.000000:1.000000, 4.000000:1.000000, 8.000000:1.000000, 10.000000:1.000000
lift_coef_at_drag_zero =0.1
lift_coef_at_drag_zero_flaps =0.1
lift_coef_air_spoilers=-0.2
elevator_lift_coef=5
rudder_lift_coef=5
fuselage_lateral_cx=0.4
drag_coef_air_spoilers=0.2
[INTERACTIVE POINTS]
number_of_interactive_points =3
interactive_point.0 =0.400000 , 7.901457 , 2.039698, -6.800532, 0 , 0.000000, 0.000000, -90.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000
interactive_point.1=0.400000 , -14.500000 , 3.261800, -5.000000, 1 , 0.000000, 0.000000, -90.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000
interactive_point.2=0.400000 , -14.500000 , 3.261800, -5.000000, 1 , 0.000000, 0.000000, -90.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000