Include tank fix
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//TFDi Designs MD-11F (GE CF6-80C2D1F) vRC1.7.0_GE_F 15MAY25
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[VERSION]
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//KH Bump major
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major = 4
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minor = 1
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[WEIGHT_AND_BALANCE]
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max_gross_weight = 630500
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empty_weight = 248567
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reference_datum_position = 0, 0, 0
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empty_weight_CG_position = -13.3, 0, 0
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CG_forward_limit = 0.12
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CG_aft_limit = 0.34
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empty_weight_pitch_MOI = 20897456
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empty_weight_roll_MOI = 6368555
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empty_weight_yaw_MOI = 40761191
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empty_weight_coupled_MOI = 0
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activate_mach_limit_based_on_cg = 0
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activate_cg_limit_based_on_mach = 0
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max_number_of_stations = 15
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//KH START Empty default
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station_load.0=0, 82.0, -2.0, 4.0, Pilot, 1
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station_load.1=0, 82.0, 2.0, 4.0, First Officer, 2
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station_load.2=0, 80.0, 3.3, 4.0, Engineer, 0
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station_load.3=0, 55.0, -5.0, 4.0, Upper zone 1 L, 0
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station_load.4=0, 55.0, 5.0, 4.0, Upper zone 1 R, 0
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station_load.5=0, 20.0, -5.0, 4.0, Upper zone 2 L, 0
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station_load.6=0, 20.0, 5.0, 4.0, Upper zone 2 R, 0
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station_load.7=0, -20.0, -5.0, 4.0, Upper zone 3 L, 0
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station_load.8=0, -20.0, 5.0, 4.0, Upper zone 3 R, 0
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station_load.9=0, -50.0, -5.0, 4.0, Upper zone 4 L, 0
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station_load.10=0, -50.0, 5.0, 4.0, Upper zone 4 R, 0
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station_load.11=0, 30.0, 0.0, -4.5, Lower forward cargo, 0
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station_load.12=0, -30.0, 0.0, -4.5, Lower rear cargo, 0
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station_load.13=0, 5.0, -2.0, -4.5, Left aux tank, 0
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station_load.14=0, 5.0, 2.0, -4.5, Right aux tank, 0
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//KH END
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[CONTACT_POINTS]
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static_pitch = 0
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static_cg_height = 16.4
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gear_system_type = 1
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tailwheel_lock = 0
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max_number_of_points = 16
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gear_locked_on_ground = 0
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gear_locked_above_speed = -1
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max_speed_full_steering = 25
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min_available_steering_angle_pct = 0.2
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max_speed_decreasing_steering = 45
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max_speed_full_steering_castering = 20
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max_speed_decreasing_steering_castering = 35
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emergency_extension_type = 2
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hyd_need_power_to_function= 0
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min_castering_angle = 0.05236
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max_castering_angle = 1.32645
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allow_stopped_steering = 1
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point.0 = 1, 64.22, 0.00, -17.31, 1500, 0, 1.67, 70, 1.15, 1.183, 0.9, 49, 50, 0, 200, 250, 8
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point.1 = 1, -19.00, -17.15, -18.02, 2000, 1, 2.25, 0, 1.60, 1.116, 0.9, 51, 52, 2, 200, 250, 8
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point.2 = 1, -19.00, 17.15, -18.02, 2000, 2, 2.25, 0, 1.60, 1.116, 0.9, 53, 54, 3, 200, 250, 8
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point.3 = 1, -19.00, 0.00, -18.02, 2000, 2, 2.25, 0, 1.60, 1.116, 0.9, 55, 56, 3, 200, 250, 8
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point.4 = 2, 93.0, 0.0, 0.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
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point.5 = 2, -48, -82.5, 0.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 5, 0, 0, 1
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point.6 = 2, -48, 82.5, 0.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 6, 0, 0, 1
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point.7 = 2, 60, 0.0, -9.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
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point.8 = 2, 60, 0.0, 11.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
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point.9 = 2, 16.0, -28.00, -13.00, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
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point.10 = 2, 16.0, 28.00, -13.00, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
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point.11 = 2, -110.0, 0.00, 14.20, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
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point.12 = 2, -96.5, 0.0, 42.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
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point.13 = 2, -94.5, -30.0, 8.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
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point.14 = 2, -94.5, 30.0, 8.05, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
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point.15 = 2, -52.0, 0.0, -9.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
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[FUEL]
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LeftMain = -20.00, -38.00, -1.0, 8938, 10.00
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RightMain = -20.00, 38.00, -1.0, 8938, 10.00
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Center1 = 10.00, 0.00, -3.00, 13000.00, 10.00
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Center2 = 0.00, 0.00, -1.00, 1642.00, 10.00
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Center3 = 0.00, 0.00, -5.00, 1958.00, 11.00
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LeftTip = -39.00, -74.00, 0.00, 884.00, 10.00
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RightTip = -39.00, 74.00, 0.00, 884.00, 10.00
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External1 = -70.00, 0.00, -3.00, 2371.00, 10.00
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//KH From 5.00, -2.00, -3.00, 0.00, 10.00
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LeftAux = 5.00, -2.00, -3.00, 1917.00, 10.00
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//KH From 5.00, 2.00, -3.00, 0.00, 10.0
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RightAux = 5.00, 2.00, -3.00, 1917.00, 10.00
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fuel_type = 2
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number_of_tank_selectors = 3
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electric_pump = 0
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engine_driven_pump = 1
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manual_transfer_pump = 0
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manual_pump = 0
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anemometer_pump = 0
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fuel_dump_rate = 0.02
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default_fuel_tank_selector.1 = 1
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default_fuel_tank_selector.2 = 1
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default_fuel_tank_selector.3 = 1
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[AIRPLANE_GEOMETRY]
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wing_area = 3648
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wing_span = 170.5
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wing_root_chord = 34.68
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wing_camber = 1
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wing_thickness_ratio = 0.04
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wing_dihedral = 2.2
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wing_incidence = 1.5
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wing_twist = -0.5
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oswald_efficiency_factor = 0.72
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wing_winglets_flag = 1
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wing_sweep = 38
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wing_pos_apex_lon = 1
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wing_pos_apex_vert = -2.75
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htail_area = 920
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htail_span = 59.5
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htail_pos_lon = -88
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htail_pos_vert = 5.0
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htail_incidence = 0.8
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htail_sweep = 36.5
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htail_thickness_ratio = 0.02
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vtail_area = 760
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vtail_span = 28.1
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vtail_sweep = 43
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vtail_pos_lon = -79.5
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vtail_pos_vert = 28
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vtail_thickness_ratio = 0.03
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fuselage_length = 202.16
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fuselage_diameter = 19.75
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fuselage_center_pos = 10, 0, 1.0
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elevator_area = 327.0
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aileron_area = 225.0
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rudder_area = 190.0
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elevator_up_limit = 25
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elevator_down_limit = 15
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aileron_up_limit = 25
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aileron_down_limit = 15
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rudder_limit = 23
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rudder_trim_limit = 20
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elevator_trim_limit = 30
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spoiler_limit = 60
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spoilerons_available = 1
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aileron_to_spoileron_gain = 3
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min_ailerons_for_spoilerons = 10
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min_flaps_for_spoilerons = 0
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spoiler_extension_time = 2.0
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spoiler_handle_available = 1
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auto_spoiler_available = 1
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auto_spoiler_auto_retracts = 0
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auto_spoiler_min_speed = 72
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positive_g_limit_flaps_up = 5.0
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positive_g_limit_flaps_down = 4.0
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negative_g_limit_flaps_up = -4.0
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negative_g_limit_flaps_down = -3.0
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load_safety_factor = 1.5
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elevator_trim_neutral = -1
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aileron_to_rudder_scale = 0
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flap_to_aileron_scale = 0
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fly_by_wire = 0
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elevator_elasticity_table = 0:0.7, 87:0.3, 210:0.5, 315:0.5
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aileron_elasticity_table = 0:1, 300:0.7, 600:0.6, 1500:0.4
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rudder_elasticity_table = 0:1, 300:1, 800:1, 1000:0.7
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elevator_trim_elasticity_table = 0:0.0, 87:0.40, 240:0.60, 295:1.00, 315:1.00
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[AERODYNAMICS]
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lift_coef_pitch_rate = -8.09375
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lift_coef_daoa = 2.68359
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lift_coef_delta_elevator = -0.28906
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lift_coef_horizontal_incidence = 0.91357
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lift_coef_flaps = 1
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lift_coef_spoilers = 0
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drag_coef_zero_lift = 0.02539
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drag_coef_flaps = 0.1889
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drag_coef_gear = 0.0549
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drag_coef_spoilers = 0.05207
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side_force_slip_angle = -0.77392
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side_force_roll_rate = 0.15478
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side_force_yaw_rate = 0
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side_force_delta_rudder = -0.14746
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pitch_moment_horizontal_incidence = 4.24755
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pitch_moment_delta_elevator = -2.37011
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pitch_moment_delta_trim = 0
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pitch_moment_pitch_damping = -214.1455
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pitch_moment_aoa_0 = 0.11621
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pitch_moment_daoa = 8.87255
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pitch_moment_flaps = 0.0105
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pitch_moment_gear = 0.0171
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pitch_moment_spoilers = 0
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pitch_moment_delta_elevator_propwash = -2.37011
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pitch_moment_pitch_propwash = -214.1455
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roll_moment_slip_angle = 0.26855
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roll_moment_roll_damping = -3.40869
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roll_moment_yaw_rate = -0.27197
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roll_moment_spoilers = 0.07
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roll_moment_delta_aileron = -0.34521
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roll_moment_delta_rudder = 0.01660
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roll_moment_delta_aileron_trim_scalar = -0.2
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yaw_moment_slip_angle = 0.18066
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yaw_moment_roll = 0.07470
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yaw_moment_yaw_damping = -2.49023
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yaw_moment_yaw_propwash = 0
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yaw_moment_delta_aileron = -0.00683
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yaw_moment_delta_rudder = 0.07128
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yaw_moment_delta_rudder_propwash = 0.075
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yaw_moment_delta_rudder_trim_scalar = -0.2
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compute_aero_center = 0
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aero_center_lift = -13.75
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lift_coef_aoa_table = -3.15:0, -2.36:0.36, -1.57:0, -0.349:-1.2, 0:-0.022, 0.0314:0.6082, 0.221:2.049, 0.244:1.15, 0.349:0.6, 0.436:0.5, 0.698:0.1, 1.963:-0.359, 2.356:-0.5, 3.15:0
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lift_coef_ground_effect_mach_table = 0.06:0.50, 0.227:0.80, 0.242:0.80, 0.3:1.0, 0.9:1.0
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lift_coef_mach_table = 0:1
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lift_coef_delta_elevator_mach_table = 0:0
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lift_coef_daoa_mach_table = 0:0
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lift_coef_pitch_rate_mach_table = 0:0
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lift_coef_horizontal_incidence_mach_table = 0:0
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drag_coef_zero_lift_mach_tab = 0:0, 0.4:0.0054, 0.5:0.0056, 0.6:0.0059, 0.7:0.0062, 0.72:0.0062, 0.8:0.0063, 0.8:0.0063, 1:0.0337, 1.2:0.0337, 1.4:0.0337, 1.6:0.0337, 1.8:0.0337, 2.0:0.0337
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side_force_slip_angle_mach_table = 0:0
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side_force_delta_rudder_mach_table = 0:0
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side_force_yaw_rate_mach_table = 0:0
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side_force_roll_rate_mach_table = 0:0
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pitch_moment_aoa_table = -3.15:-2, -0.436:-0.626, -0.262:-0.434, 0:-0.146, 0.087:-0.05, 0.175:0.0466, 0.262:0.143, 0.314:0.2, 0.349:0.1, 0.436:0.15, 3.15:2
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pitch_moment_delta_elevator_aoa_table = -180:-1, -40:0.05, -20:0.455, -14:0.853, -7:1.007, 0:1, 7:0.839, 14:0.693, 20:0.381, 40:-0.08, 180:-1
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pitch_moment_horizontal_incidence_aoa_table = 0:1
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pitch_moment_daoa_aoa_table = 0:1
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pitch_moment_pitch_alpha_table = 0:1
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pitch_moment_delta_elevator_mach_table = 0:0
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pitch_moment_daoa_mach_table = 0:0
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pitch_moment_pitch_rate_mach_table = 0:0
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pitch_moment_horizontal_incidence_mach_table = 0:0
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pitch_moment_aoa_0_mach_table = 0:0
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roll_moment_aoa_table = 0:0
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roll_moment_slip_angle_aoa_table = 0:1
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roll_moment_roll_rate_aoa_table = 0:1
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roll_moment_delta_aileron_aoa_table = 0:1
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roll_moment_slip_angle_mach_table = 0:0
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roll_moment_delta_rudder_mach_table = 0:0
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roll_moment_delta_aileron_mach_table = 0:0
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roll_moment_yaw_rate_mach_table = 0:0
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roll_moment_roll_rate_mach_table = 0:0
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yaw_moment_aoa_table = 0:0
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yaw_moment_slip_angle_aoa_table = 0:1
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yaw_moment_yaw_rate_aoa_table = 0:1
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yaw_moment_delta_rudder_aoa_table = 0:1
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yaw_moment_slip_angle_mach_table = 0:0
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yaw_moment_delta_rudder_mach_table = 0:0
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yaw_moment_delta_aileron_mach_table = 0:0
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yaw_moment_yaw_rate_mach_table = 0:0
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yaw_moment_roll_rate_mach_table = 0:0
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elevator_scaling_table = -0.785:0.5, -0.524:0.85, -0.175:0.9, 0:1, 0.175:0.9, 0.524:0.85, 0.785:0.5 ; 0:1
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aileron_scaling_table = -0.785:1 ;0:1
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rudder_scaling_table = -0.785:0.5, -0.524:0.6, -0.175:0.9, 0:1, 0.175:0.9, 0.524:0.6, 0.785:0.5 ;0:1
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elevator_lift_coef=3
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rudder_lift_coef=2
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aileron_load_factor_effectiveness_table = 0:1
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lift_coef_at_drag_zero = 0.1
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lift_coef_at_drag_zero_flaps = 0.1
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[FLIGHT_TUNING]
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modern_fm_only = 1
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cruise_lift_scalar = 1
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parasite_drag_scalar = 1
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induced_drag_scalar = 1
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flap_induced_drag_scalar = 1
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elevator_effectiveness = 1
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elevator_maxangle_scalar = 1
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aileron_effectiveness = 1
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rudder_effectiveness = 1
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rudder_maxangle_scalar = 1
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pitch_stability = 5
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roll_stability = 1
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yaw_stability = 1
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pitch_gyro_stability = 1
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roll_gyro_stability = 1
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yaw_gyro_stability = 1
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empty_CG_deviation_limit=0
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elevator_trim_effectiveness = 1.5
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aileron_trim_effectiveness = 1
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rudder_trim_effectiveness = 1
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hi_alpha_on_roll = 0
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hi_alpha_on_yaw = 0
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p_factor_on_yaw = 0
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torque_on_roll = 0
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gyro_precession_on_roll = 0
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gyro_precession_on_yaw = 0
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engine_wash_on_roll = 0
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wingflex_scalar = 2
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wingflex_offset = 0
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stall_coef_at_min_weight = 0.71
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ground_crosswind_effect_zero_speed=10
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ground_crosswind_effect_max_speed=150
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ground_high_speed_steeringwheel_static_friction_scalar=1.5
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ground_high_speed_otherwheel_static_friction_scalar=1.2
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[REFERENCE SPEEDS]
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full_flaps_stall_speed = 115
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flaps_up_stall_speed = 149
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cruise_speed = 345
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cruise_mach = 0.85
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crossover_speed = 330
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max_mach = 0.9
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max_indicated_speed = 395
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max_flaps_extended = 170
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normal_operating_speed = 325
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airspeed_indicator_max = 562.5
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rotation_speed_min = 145
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climb_speed = 250
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cruise_alt = 41000
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takeoff_speed = 165
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spawn_cruise_altitude = 5000
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spawn_descent_altitude = 500
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best_angle_climb_speed = 0
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approach_speed = 0
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best_glide = 0
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max_gear_extended = 200
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[INTERACTIVE POINTS]
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number_of_interactive_points = 2
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interactive_point.0 = 0.4, 75.65, -8.12, -0.567, 0, 0, 0, -75, 33, 2, 33, 2, 2, 33
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interactive_point.1 = 0.4, 33.3, 6.28, -7.18, 1, 0, 0, 90, 0, 0, 0, 0, 0, 0
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[STALL PROTECTION]
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stall_protection = 1 ; Alpha Protection
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off_limit = 11.5 ; Alpha below which the Alpha Protection can be disabled (If also below off_yoke_limit)
|
||||
off_yoke_limit = 1 ; Yoke position (in Pct) below which the Alpha Protection can be disabled (If also below off_limit)
|
||||
on_limit = 14 ; Alpha above which the Alpha Protection timer starts
|
||||
on_goal = 10 ; The alpha that the Alpha Protection will attempt to reach when triggered
|
||||
timer_trigger = 1.0 ; Duration (in Sec) the alpha must be above on_limit before the Alpha Protection is triggered
|
||||
|
||||
;===================== FLAPS =====================
|
||||
|
||||
[FLAPS.0]
|
||||
type = 1
|
||||
system_type = 1
|
||||
span-outboard = 0.25
|
||||
extending-time = 22
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.1
|
||||
drag_scalar = 1.1
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 7
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 0, -1, 0
|
||||
flaps-position.2 = 15, 215, 0.25, 2, 0, 0, 0, 1
|
||||
flaps-position.3 = 20, 200, 0.26, 1.1, 0, 0, 0, 1
|
||||
flaps-position.4 = 24, 185, 0.28, 1.0, 0, 0, 0, 1
|
||||
flaps-position.5 = 28, 177, 0.3, 1.0, 1.5, 0, 0
|
||||
flaps-position.6 = 35, 160, 0.32, 1
|
||||
flaps-position.7 = 50, 150, 0.33, 1
|
||||
|
||||
[FLAPS.1]
|
||||
type = 1
|
||||
system_type = 1
|
||||
span-outboard = 0.7
|
||||
extending-time = 23
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.1
|
||||
drag_scalar = 1.1
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 7
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 0, -1, 0
|
||||
flaps-position.2 = 15, 215, 0.25, 2, 0, 0, 0, 1
|
||||
flaps-position.3 = 20, 200, 0.26, 1.1, 0, 0, 0, 1
|
||||
flaps-position.4 = 24, 185, 0.28, 1.0, 0, 0, 0, 1
|
||||
flaps-position.5 = 28, 177, 0.3, 1.0, 1.5, 0, 0
|
||||
flaps-position.6 = 35, 160, 0.32, 1
|
||||
flaps-position.7 = 50, 150, 0.33, 1
|
||||
|
||||
[FLAPS.2]
|
||||
type = 2
|
||||
system_type = 1
|
||||
span-outboard = 0.2
|
||||
extending-time = 8
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.5
|
||||
drag_scalar = 0.75
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 1
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 20, 215, 0.5, 0.5
|
||||
|
||||
[FLAPS.3]
|
||||
type = 2
|
||||
system_type = 1
|
||||
span-outboard = 0.7
|
||||
extending-time = 21
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.5
|
||||
drag_scalar = 0.75
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 1
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 20, 215, 0.5, 0.5
|
||||
@ -0,0 +1,399 @@
|
||||
//TFDi Designs MD-11F (P&W PW4660) vRC1.7.0_PW_F 15MAY25
|
||||
|
||||
[VERSION]
|
||||
//KH Bump major
|
||||
major = 4
|
||||
minor = 1
|
||||
|
||||
[WEIGHT_AND_BALANCE]
|
||||
max_gross_weight = 630500
|
||||
empty_weight = 248567
|
||||
reference_datum_position = 0, 0, 0
|
||||
empty_weight_CG_position = -13.3, 0, 0
|
||||
CG_forward_limit = 0.12
|
||||
CG_aft_limit = 0.34
|
||||
empty_weight_pitch_MOI = 20897456
|
||||
empty_weight_roll_MOI = 6368555
|
||||
empty_weight_yaw_MOI = 40761191
|
||||
empty_weight_coupled_MOI = 0
|
||||
activate_mach_limit_based_on_cg = 0
|
||||
activate_cg_limit_based_on_mach = 0
|
||||
max_number_of_stations = 15
|
||||
//KH START Empty default
|
||||
station_load.0=0, 82.0, -2.0, 4.0, Pilot, 1
|
||||
station_load.1=0, 82.0, 2.0, 4.0, First Officer, 2
|
||||
station_load.2=0, 80.0, 3.3, 4.0, Engineer, 0
|
||||
station_load.3=0, 55.0, -5.0, 4.0, Upper zone 1 L, 0
|
||||
station_load.4=0, 55.0, 5.0, 4.0, Upper zone 1 R, 0
|
||||
station_load.5=0, 20.0, -5.0, 4.0, Upper zone 2 L, 0
|
||||
station_load.6=0, 20.0, 5.0, 4.0, Upper zone 2 R, 0
|
||||
station_load.7=0, -20.0, -5.0, 4.0, Upper zone 3 L, 0
|
||||
station_load.8=0, -20.0, 5.0, 4.0, Upper zone 3 R, 0
|
||||
station_load.9=0, -50.0, -5.0, 4.0, Upper zone 4 L, 0
|
||||
station_load.10=0, -50.0, 5.0, 4.0, Upper zone 4 R, 0
|
||||
station_load.11=0, 30.0, 0.0, -4.5, Lower forward cargo, 0
|
||||
station_load.12=0, -30.0, 0.0, -4.5, Lower rear cargo, 0
|
||||
station_load.13=0, 5.0, -2.0, -4.5, Left aux tank, 0
|
||||
station_load.14=0, 5.0, 2.0, -4.5, Right aux tank, 0
|
||||
//KH END
|
||||
|
||||
[CONTACT_POINTS]
|
||||
static_pitch = 0
|
||||
static_cg_height = 16.4
|
||||
gear_system_type = 1
|
||||
tailwheel_lock = 0
|
||||
max_number_of_points = 16
|
||||
gear_locked_on_ground = 0
|
||||
gear_locked_above_speed = -1
|
||||
max_speed_full_steering = 25
|
||||
min_available_steering_angle_pct = 0.2
|
||||
max_speed_decreasing_steering = 45
|
||||
max_speed_full_steering_castering = 20
|
||||
max_speed_decreasing_steering_castering = 35
|
||||
emergency_extension_type = 2
|
||||
hyd_need_power_to_function= 0
|
||||
min_castering_angle = 0.05236
|
||||
max_castering_angle = 1.32645
|
||||
allow_stopped_steering = 1
|
||||
point.0 = 1, 64.22, 0.00, -17.31, 1500, 0, 1.67, 70, 1.15, 1.183, 0.9, 49, 50, 0, 200, 250, 8
|
||||
point.1 = 1, -19.00, -17.15, -18.02, 2000, 1, 2.25, 0, 1.60, 1.116, 0.9, 51, 52, 2, 200, 250, 8
|
||||
point.2 = 1, -19.00, 17.15, -18.02, 2000, 2, 2.25, 0, 1.60, 1.116, 0.9, 53, 54, 3, 200, 250, 8
|
||||
point.3 = 1, -19.00, 0.00, -18.02, 2000, 2, 2.25, 0, 1.60, 1.116, 0.9, 55, 56, 3, 200, 250, 8
|
||||
point.4 = 2, 93.0, 0.0, 0.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
|
||||
point.5 = 2, -48, -82.5, 0.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 5, 0, 0, 1
|
||||
point.6 = 2, -48, 82.5, 0.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 6, 0, 0, 1
|
||||
point.7 = 2, 60, 0.0, -9.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
|
||||
point.8 = 2, 60, 0.0, 11.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
|
||||
point.9 = 2, 16.0, -28.00, -13.00, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.10 = 2, 16.0, 28.00, -13.00, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.11 = 2, -110.0, 0.00, 14.20, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.12 = 2, -96.5, 0.0, 42.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.13 = 2, -94.5, -30.0, 8.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.14 = 2, -94.5, 30.0, 8.05, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.15 = 2, -52.0, 0.0, -9.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
|
||||
|
||||
[FUEL]
|
||||
LeftMain = -20.00, -38.00, -1.0, 8938, 10.00
|
||||
RightMain = -20.00, 38.00, -1.0, 8938, 10.00
|
||||
Center1 = 10.00, 0.00, -3.00, 13000.00, 10.00
|
||||
Center2 = 0.00, 0.00, -1.00, 1642.00, 10.00
|
||||
Center3 = 0.00, 0.00, -5.00, 1958.00, 11.00
|
||||
LeftTip = -39.00, -74.00, 0.00, 884.00, 10.00
|
||||
RightTip = -39.00, 74.00, 0.00, 884.00, 10.00
|
||||
External1 = -70.00, 0.00, -3.00, 2371.00, 10.00
|
||||
//KH From 5.00, -2.00, -3.00, 0.00, 10.00
|
||||
LeftAux = 5.00, -2.00, -3.00, 1917.00, 10.00
|
||||
//KH From 5.00, 2.00, -3.00, 0.00, 10.0
|
||||
RightAux = 5.00, 2.00, -3.00, 1917.00, 10.00
|
||||
fuel_type = 2
|
||||
number_of_tank_selectors = 3
|
||||
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_tank_selector.2 = 1
|
||||
default_fuel_tank_selector.3 = 1
|
||||
|
||||
[AIRPLANE_GEOMETRY]
|
||||
wing_area = 3648
|
||||
wing_span = 170.5
|
||||
wing_root_chord = 34.68
|
||||
wing_camber = 1
|
||||
wing_thickness_ratio = 0.04
|
||||
wing_dihedral = 2.2
|
||||
wing_incidence = 1.5
|
||||
wing_twist = -0.5
|
||||
oswald_efficiency_factor = 0.72
|
||||
wing_winglets_flag = 1
|
||||
wing_sweep = 38
|
||||
wing_pos_apex_lon = 1
|
||||
wing_pos_apex_vert = -2.75
|
||||
htail_area = 920
|
||||
htail_span = 59.5
|
||||
htail_pos_lon = -88
|
||||
htail_pos_vert = 5.0
|
||||
htail_incidence = 0.8
|
||||
htail_sweep = 36.5
|
||||
htail_thickness_ratio = 0.02
|
||||
vtail_area = 760
|
||||
vtail_span = 28.1
|
||||
vtail_sweep = 43
|
||||
vtail_pos_lon = -79.5
|
||||
vtail_pos_vert = 28
|
||||
vtail_thickness_ratio = 0.03
|
||||
fuselage_length = 200.92
|
||||
fuselage_diameter = 19.75
|
||||
fuselage_center_pos = 10, 0, 1.0
|
||||
elevator_area = 327.0
|
||||
aileron_area = 225.0
|
||||
rudder_area = 190.0
|
||||
elevator_up_limit = 25
|
||||
elevator_down_limit = 15
|
||||
aileron_up_limit = 25
|
||||
aileron_down_limit = 15
|
||||
rudder_limit = 23
|
||||
rudder_trim_limit = 20
|
||||
elevator_trim_limit = 30
|
||||
spoiler_limit = 60
|
||||
spoilerons_available = 1
|
||||
aileron_to_spoileron_gain = 3
|
||||
min_ailerons_for_spoilerons = 10
|
||||
min_flaps_for_spoilerons = 0
|
||||
spoiler_extension_time = 2.0
|
||||
spoiler_handle_available = 1
|
||||
auto_spoiler_available = 1
|
||||
auto_spoiler_auto_retracts = 0
|
||||
auto_spoiler_min_speed = 72
|
||||
positive_g_limit_flaps_up = 5.0
|
||||
positive_g_limit_flaps_down = 4.0
|
||||
negative_g_limit_flaps_up = -4.0
|
||||
negative_g_limit_flaps_down = -3.0
|
||||
load_safety_factor = 1.5
|
||||
elevator_trim_neutral = -1
|
||||
aileron_to_rudder_scale = 0
|
||||
flap_to_aileron_scale = 0
|
||||
fly_by_wire = 0
|
||||
elevator_elasticity_table = 0:0.7, 87:0.3, 210:0.5, 315:0.5
|
||||
aileron_elasticity_table = 0:1, 300:0.7, 600:0.6, 1500:0.4
|
||||
rudder_elasticity_table = 0:1, 300:1, 800:1, 1000:0.7
|
||||
elevator_trim_elasticity_table = 0:0.0, 87:0.40, 240:0.60, 295:1.00, 315:1.00
|
||||
|
||||
[AERODYNAMICS]
|
||||
lift_coef_pitch_rate = -8.09375
|
||||
lift_coef_daoa = 2.68359
|
||||
lift_coef_delta_elevator = -0.28906
|
||||
lift_coef_horizontal_incidence = 0.91357
|
||||
lift_coef_flaps = 1
|
||||
lift_coef_spoilers = 0
|
||||
drag_coef_zero_lift = 0.02539
|
||||
drag_coef_flaps = 0.1889
|
||||
drag_coef_gear = 0.0549
|
||||
drag_coef_spoilers = 0.05207
|
||||
side_force_slip_angle = -0.77392
|
||||
side_force_roll_rate = 0.15478
|
||||
side_force_yaw_rate = 0
|
||||
side_force_delta_rudder = -0.14746
|
||||
pitch_moment_horizontal_incidence = 4.24755
|
||||
pitch_moment_delta_elevator = -2.37011
|
||||
pitch_moment_delta_trim = 0
|
||||
pitch_moment_pitch_damping = -214.1455
|
||||
pitch_moment_aoa_0 = 0.11621
|
||||
pitch_moment_daoa = 8.87255
|
||||
pitch_moment_flaps = 0.0105
|
||||
pitch_moment_gear = 0.0171
|
||||
pitch_moment_spoilers = 0
|
||||
pitch_moment_delta_elevator_propwash = -2.37011
|
||||
pitch_moment_pitch_propwash = -214.1455
|
||||
roll_moment_slip_angle = 0.26855
|
||||
roll_moment_roll_damping = -3.40869
|
||||
roll_moment_yaw_rate = -0.27197
|
||||
roll_moment_spoilers = 0.07
|
||||
roll_moment_delta_aileron = -0.34521
|
||||
roll_moment_delta_rudder = 0.01660
|
||||
roll_moment_delta_aileron_trim_scalar = -0.2
|
||||
yaw_moment_slip_angle = 0.18066
|
||||
yaw_moment_roll = 0.07470
|
||||
yaw_moment_yaw_damping = -2.49023
|
||||
yaw_moment_yaw_propwash = 0
|
||||
yaw_moment_delta_aileron = -0.00683
|
||||
yaw_moment_delta_rudder = 0.07128
|
||||
yaw_moment_delta_rudder_propwash = 0.075
|
||||
yaw_moment_delta_rudder_trim_scalar = -0.2
|
||||
compute_aero_center = 0
|
||||
aero_center_lift = -13.75
|
||||
lift_coef_aoa_table = -3.15:0, -2.36:0.36, -1.57:0, -0.349:-1.2, 0:-0.022, 0.0314:0.6082, 0.221:2.049, 0.244:1.15, 0.349:0.6, 0.436:0.5, 0.698:0.1, 1.963:-0.359, 2.356:-0.5, 3.15:0
|
||||
lift_coef_ground_effect_mach_table = 0.06:0.50, 0.227:0.80, 0.242:0.80, 0.3:1.0, 0.9:1.0
|
||||
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, 0.4:0.0054, 0.5:0.0056, 0.6:0.0059, 0.7:0.0062, 0.72:0.0062, 0.8:0.0063, 0.8:0.0063, 1:0.0337, 1.2:0.0337, 1.4:0.0337, 1.6:0.0337, 1.8:0.0337, 2.0:0.0337
|
||||
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:-2, -0.436:-0.626, -0.262:-0.434, 0:-0.146, 0.087:-0.05, 0.175:0.0466, 0.262:0.143, 0.314:0.2, 0.349:0.1, 0.436:0.15, 3.15:2
|
||||
pitch_moment_delta_elevator_aoa_table = -180:-1, -40:0.05, -20:0.455, -14:0.853, -7:1.007, 0:1, 7:0.839, 14:0.693, 20:0.381, 40:-0.08, 180:-1
|
||||
pitch_moment_horizontal_incidence_aoa_table = 0:1
|
||||
pitch_moment_daoa_aoa_table = 0:1
|
||||
pitch_moment_pitch_alpha_table = 0:1
|
||||
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
|
||||
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
|
||||
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 = -0.785:0.5, -0.524:0.85, -0.175:0.9, 0:1, 0.175:0.9, 0.524:0.85, 0.785:0.5 ; 0:1
|
||||
aileron_scaling_table = -0.785:1 ;0:1
|
||||
rudder_scaling_table = -0.785:0.5, -0.524:0.6, -0.175:0.9, 0:1, 0.175:0.9, 0.524:0.6, 0.785:0.5 ;0:1
|
||||
elevator_lift_coef=3
|
||||
rudder_lift_coef=2
|
||||
aileron_load_factor_effectiveness_table = 0:1
|
||||
lift_coef_at_drag_zero = 0.1
|
||||
lift_coef_at_drag_zero_flaps = 0.1
|
||||
|
||||
[FLIGHT_TUNING]
|
||||
modern_fm_only = 1
|
||||
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 = 5
|
||||
roll_stability = 1
|
||||
yaw_stability = 1
|
||||
pitch_gyro_stability = 1
|
||||
roll_gyro_stability = 1
|
||||
yaw_gyro_stability = 1
|
||||
empty_CG_deviation_limit=0
|
||||
elevator_trim_effectiveness = 1.5
|
||||
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
|
||||
wingflex_scalar = 2
|
||||
wingflex_offset = 0
|
||||
stall_coef_at_min_weight = 0.71
|
||||
ground_crosswind_effect_zero_speed=10
|
||||
ground_crosswind_effect_max_speed=150
|
||||
ground_high_speed_steeringwheel_static_friction_scalar=1.5
|
||||
ground_high_speed_otherwheel_static_friction_scalar=1.2
|
||||
|
||||
[REFERENCE SPEEDS]
|
||||
full_flaps_stall_speed = 115
|
||||
flaps_up_stall_speed = 149
|
||||
cruise_speed = 345
|
||||
cruise_mach = 0.85
|
||||
crossover_speed = 330
|
||||
max_mach = 0.9
|
||||
max_indicated_speed = 395
|
||||
max_flaps_extended = 170
|
||||
normal_operating_speed = 325
|
||||
airspeed_indicator_max = 562.5
|
||||
rotation_speed_min = 145
|
||||
climb_speed = 250
|
||||
cruise_alt = 41000
|
||||
takeoff_speed = 165
|
||||
spawn_cruise_altitude = 5000
|
||||
spawn_descent_altitude = 500
|
||||
best_angle_climb_speed = 0
|
||||
approach_speed = 0
|
||||
best_glide = 0
|
||||
max_gear_extended = 200
|
||||
|
||||
[INTERACTIVE POINTS]
|
||||
number_of_interactive_points = 2
|
||||
interactive_point.0 = 0.4, 75.65, -8.12, -0.567, 0, 0, 0, -75, 33, 2, 33, 2, 2, 33
|
||||
interactive_point.1 = 0.4, 33.3, 6.28, -7.18, 1, 0, 0, 90, 0, 0, 0, 0, 0, 0
|
||||
|
||||
[STALL PROTECTION]
|
||||
stall_protection = 1 ; Alpha Protection
|
||||
off_limit = 11.5 ; Alpha below which the Alpha Protection can be disabled (If also below off_yoke_limit)
|
||||
off_yoke_limit = 1 ; Yoke position (in Pct) below which the Alpha Protection can be disabled (If also below off_limit)
|
||||
on_limit = 14 ; Alpha above which the Alpha Protection timer starts
|
||||
on_goal = 10 ; The alpha that the Alpha Protection will attempt to reach when triggered
|
||||
timer_trigger = 1.0 ; Duration (in Sec) the alpha must be above on_limit before the Alpha Protection is triggered
|
||||
|
||||
;===================== FLAPS =====================
|
||||
|
||||
[FLAPS.0]
|
||||
type = 1
|
||||
system_type = 1
|
||||
span-outboard = 0.25
|
||||
extending-time = 22
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.1
|
||||
drag_scalar = 1.1
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 7
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 0, -1, 0
|
||||
flaps-position.2 = 15, 215, 0.25, 2, 0, 0, 0, 1
|
||||
flaps-position.3 = 20, 200, 0.26, 1.1, 0, 0, 0, 1
|
||||
flaps-position.4 = 24, 185, 0.28, 1.0, 0, 0, 0, 1
|
||||
flaps-position.5 = 28, 177, 0.3, 1.0, 1.5, 0, 0
|
||||
flaps-position.6 = 35, 160, 0.32, 1
|
||||
flaps-position.7 = 50, 150, 0.33, 1
|
||||
|
||||
[FLAPS.1]
|
||||
type = 1
|
||||
system_type = 1
|
||||
span-outboard = 0.7
|
||||
extending-time = 23
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.1
|
||||
drag_scalar = 1.1
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 7
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 0, -1, 0
|
||||
flaps-position.2 = 15, 215, 0.25, 2, 0, 0, 0, 1
|
||||
flaps-position.3 = 20, 200, 0.26, 1.1, 0, 0, 0, 1
|
||||
flaps-position.4 = 24, 185, 0.28, 1.0, 0, 0, 0, 1
|
||||
flaps-position.5 = 28, 177, 0.3, 1.0, 1.5, 0, 0
|
||||
flaps-position.6 = 35, 160, 0.32, 1
|
||||
flaps-position.7 = 50, 150, 0.33, 1
|
||||
|
||||
[FLAPS.2]
|
||||
type = 2
|
||||
system_type = 1
|
||||
span-outboard = 0.2
|
||||
extending-time = 8
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.5
|
||||
drag_scalar = 0.75
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 1
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 20, 215, 0.5, 0.5
|
||||
|
||||
[FLAPS.3]
|
||||
type = 2
|
||||
system_type = 1
|
||||
span-outboard = 0.7
|
||||
extending-time = 21
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.5
|
||||
drag_scalar = 0.75
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 1
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 20, 215, 0.5, 0.5
|
||||
@ -0,0 +1,408 @@
|
||||
//TFDi Designs MD-11 (GE CF6-80C2D1F) vRC1.7.0_GE 15MAY25
|
||||
|
||||
[VERSION]
|
||||
//KH Bump major
|
||||
major = 4
|
||||
minor = 1
|
||||
|
||||
[WEIGHT_AND_BALANCE]
|
||||
max_gross_weight = 630500
|
||||
empty_weight = 283975
|
||||
reference_datum_position = 0, 0, 0
|
||||
empty_weight_CG_position = -13.3, 0, 0
|
||||
CG_forward_limit = 0.12
|
||||
CG_aft_limit = 0.34
|
||||
empty_weight_pitch_MOI = 20897456
|
||||
empty_weight_roll_MOI = 6368555
|
||||
empty_weight_yaw_MOI = 40761191
|
||||
empty_weight_coupled_MOI = 0
|
||||
activate_mach_limit_based_on_cg = 0
|
||||
activate_cg_limit_based_on_mach = 0
|
||||
max_number_of_stations = 21
|
||||
//KH START Empty default
|
||||
station_load.0=0, 82.0, -2.0, 4.0, Pilot, 1
|
||||
station_load.1=0, 82.0, 2.0, 4.0, First Officer, 2
|
||||
station_load.2=0, 80.0, 3.3, 4.0, Engineer, 0
|
||||
station_load.3=0, 66.0, 0.0, 4.0, Cabin crew 1, 0
|
||||
station_load.4=0, 45.0, -5.0, 4.0, Business 1 L, 0
|
||||
station_load.5=0, 45.0, 0.0, 4.0, Business 1 C, 0
|
||||
station_load.6=0, 45.0, 5.0, 4.0, Business 1 R, 0
|
||||
station_load.7=0, 25.0, -5.0, 4.0, Business 2 L, 0
|
||||
station_load.8=0, 25.0, 0.0, 4.0, Business 2 C, 0
|
||||
station_load.9=0, 25.0, 5.0, 4.0, Business 2 R, 0
|
||||
station_load.10=0, -20.0, -5.0, 4.0, Economy 3 L, 0
|
||||
station_load.11=0, -20.0, 0.0, 4.0, Economy 3 C, 0
|
||||
station_load.12=0, -20.0, 5.0, 4.0, Economy 3 R, 0
|
||||
station_load.13=0, -50.0, -5.0, 4.0, Economy 4 L, 0
|
||||
station_load.14=0, -50.0, 0.0, 4.0, Economy 4 C, 0
|
||||
station_load.15=0, -50.0, 5.0, 4.0, Economy 4 R, 0
|
||||
station_load.16=0, -55.0, 0.0, 4.0, Cabin crew 2, 0
|
||||
station_load.17=0, 30.0, 0.0, -4.5, Forward cargo, 0
|
||||
station_load.18=0, -30.0, 0.0, -4.5, Rear cargo, 0
|
||||
station_load.19=0, 5.0, -2.0, -4.5, Left aux tank, 0
|
||||
station_load.20=0, 5.0, 2.0, -4.5, Right aux tank, 0
|
||||
//KH END
|
||||
|
||||
[CONTACT_POINTS]
|
||||
static_pitch = 0
|
||||
static_cg_height = 16.4
|
||||
gear_system_type = 1
|
||||
tailwheel_lock = 0
|
||||
max_number_of_points = 16
|
||||
gear_locked_on_ground = 0
|
||||
gear_locked_above_speed = -1
|
||||
max_speed_full_steering = 25
|
||||
min_available_steering_angle_pct = 0.2
|
||||
max_speed_decreasing_steering = 45
|
||||
max_speed_full_steering_castering = 20
|
||||
max_speed_decreasing_steering_castering = 35
|
||||
emergency_extension_type = 2
|
||||
hyd_need_power_to_function= 0
|
||||
min_castering_angle = 0.05236
|
||||
max_castering_angle = 1.32645
|
||||
allow_stopped_steering = 1
|
||||
point.0 = 1, 64.22, 0.00, -17.31, 1500, 0, 1.67, 70, 1.15, 1.183, 0.9, 49, 50, 0, 200, 250, 8
|
||||
point.1 = 1, -19.00, -17.15, -18.02, 2000, 1, 2.25, 0, 1.60, 1.116, 0.9, 51, 52, 2, 200, 250, 8
|
||||
point.2 = 1, -19.00, 17.15, -18.02, 2000, 2, 2.25, 0, 1.60, 1.116, 0.9, 53, 54, 3, 200, 250, 8
|
||||
point.3 = 1, -19.00, 0.00, -18.02, 2000, 2, 2.25, 0, 1.60, 1.116, 0.9, 55, 56, 3, 200, 250, 8
|
||||
point.4 = 2, 93.0, 0.0, 0.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
|
||||
point.5 = 2, -48, -82.5, 0.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 5, 0, 0, 1
|
||||
point.6 = 2, -48, 82.5, 0.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 6, 0, 0, 1
|
||||
point.7 = 2, 60, 0.0, -9.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
|
||||
point.8 = 2, 60, 0.0, 11.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
|
||||
point.9 = 2, 16.0, -28.00, -13.00, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.10 = 2, 16.0, 28.00, -13.00, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.11 = 2, -110.0, 0.00, 14.20, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.12 = 2, -96.5, 0.0, 42.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.13 = 2, -94.5, -30.0, 8.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.14 = 2, -94.5, 30.0, 8.05, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.15 = 2, -52.0, 0.0, -9.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
|
||||
|
||||
[FUEL]
|
||||
LeftMain = -20.00, -38.00, -1.0, 8938, 10.00
|
||||
RightMain = -20.00, 38.00, -1.0, 8938, 10.00
|
||||
Center1 = 10.00, 0.00, -3.00, 13000.00, 10.00
|
||||
Center2 = 0.00, 0.00, -1.00, 1642.00, 10.00
|
||||
Center3 = 0.00, 0.00, -5.00, 1958.00, 11.00
|
||||
LeftTip = -39.00, -74.00, 0.00, 884.00, 10.00
|
||||
RightTip = -39.00, 74.00, 0.00, 884.00, 10.00
|
||||
External1 = -70.00, 0.00, -3.00, 2371.00, 10.00
|
||||
//KH From 5.00, -2.00, -3.00, 0.00, 10.00
|
||||
LeftAux = 5.00, -2.00, -3.00, 1917.00, 10.00
|
||||
//KH From 5.00, 2.00, -3.00, 0.00, 10.0
|
||||
RightAux = 5.00, 2.00, -3.00, 1917.00, 10.00
|
||||
fuel_type = 2
|
||||
number_of_tank_selectors = 3
|
||||
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_tank_selector.2 = 1
|
||||
default_fuel_tank_selector.3 = 1
|
||||
|
||||
[AIRPLANE_GEOMETRY]
|
||||
wing_area = 3648
|
||||
wing_span = 170.5
|
||||
wing_root_chord = 34.68
|
||||
wing_camber = 1
|
||||
wing_thickness_ratio = 0.04
|
||||
wing_dihedral = 2.2
|
||||
wing_incidence = 1.5
|
||||
wing_twist = -0.5
|
||||
oswald_efficiency_factor = 0.72
|
||||
wing_winglets_flag = 1
|
||||
wing_sweep = 38
|
||||
wing_pos_apex_lon = 1
|
||||
wing_pos_apex_vert = -2.75
|
||||
htail_area = 920
|
||||
htail_span = 59.5
|
||||
htail_pos_lon = -88
|
||||
htail_pos_vert = 5.0
|
||||
htail_incidence = 0.8
|
||||
htail_sweep = 36.5
|
||||
htail_thickness_ratio = 0.02
|
||||
vtail_area = 760
|
||||
vtail_span = 28.1
|
||||
vtail_sweep = 43
|
||||
vtail_pos_lon = -79.5
|
||||
vtail_pos_vert = 28
|
||||
vtail_thickness_ratio = 0.03
|
||||
fuselage_length = 202.16
|
||||
fuselage_diameter = 19.75
|
||||
fuselage_center_pos = 10, 0, 1.0
|
||||
elevator_area = 327.0
|
||||
aileron_area = 225.0
|
||||
rudder_area = 190.0
|
||||
elevator_up_limit = 25
|
||||
elevator_down_limit = 15
|
||||
aileron_up_limit = 25
|
||||
aileron_down_limit = 15
|
||||
rudder_limit = 23
|
||||
rudder_trim_limit = 20
|
||||
elevator_trim_limit = 30
|
||||
spoiler_limit = 60
|
||||
spoilerons_available = 1
|
||||
aileron_to_spoileron_gain = 3
|
||||
min_ailerons_for_spoilerons = 10
|
||||
min_flaps_for_spoilerons = 0
|
||||
spoiler_extension_time = 2.0
|
||||
spoiler_handle_available = 1
|
||||
auto_spoiler_available = 1
|
||||
auto_spoiler_auto_retracts = 0
|
||||
auto_spoiler_min_speed = 72
|
||||
positive_g_limit_flaps_up = 5.0
|
||||
positive_g_limit_flaps_down = 4.0
|
||||
negative_g_limit_flaps_up = -4.0
|
||||
negative_g_limit_flaps_down = -3.0
|
||||
load_safety_factor = 1.5
|
||||
elevator_trim_neutral = -1
|
||||
aileron_to_rudder_scale = 0
|
||||
flap_to_aileron_scale = 0
|
||||
fly_by_wire = 0
|
||||
elevator_elasticity_table = 0:0.7, 87:0.3, 210:0.5, 315:0.5
|
||||
aileron_elasticity_table = 0:1, 300:0.7, 600:0.6, 1500:0.4
|
||||
rudder_elasticity_table = 0:1, 300:1, 800:1, 1000:0.7
|
||||
elevator_trim_elasticity_table = 0:0.0, 87:0.40, 240:0.60, 295:1.00, 315:1.00
|
||||
|
||||
[AERODYNAMICS]
|
||||
lift_coef_pitch_rate = -8.09375
|
||||
lift_coef_daoa = 2.68359
|
||||
lift_coef_delta_elevator = -0.28906
|
||||
lift_coef_horizontal_incidence = 0.91357
|
||||
lift_coef_flaps = 1
|
||||
lift_coef_spoilers = 0
|
||||
drag_coef_zero_lift = 0.02539
|
||||
drag_coef_flaps = 0.1889
|
||||
drag_coef_gear = 0.0549
|
||||
drag_coef_spoilers = 0.05207
|
||||
side_force_slip_angle = -0.77392
|
||||
side_force_roll_rate = 0.15478
|
||||
side_force_yaw_rate = 0
|
||||
side_force_delta_rudder = -0.14746
|
||||
pitch_moment_horizontal_incidence = 4.24755
|
||||
pitch_moment_delta_elevator = -2.37011
|
||||
pitch_moment_delta_trim = 0
|
||||
pitch_moment_pitch_damping = -214.1455
|
||||
pitch_moment_aoa_0 = 0.11621
|
||||
pitch_moment_daoa = 8.87255
|
||||
pitch_moment_flaps = 0.0105
|
||||
pitch_moment_gear = 0.0171
|
||||
pitch_moment_spoilers = 0
|
||||
pitch_moment_delta_elevator_propwash = -2.37011
|
||||
pitch_moment_pitch_propwash = -214.1455
|
||||
roll_moment_slip_angle = 0.26855
|
||||
roll_moment_roll_damping = -3.40869
|
||||
roll_moment_yaw_rate = -0.27197
|
||||
roll_moment_spoilers = 0.07
|
||||
roll_moment_delta_aileron = -0.34521
|
||||
roll_moment_delta_rudder = 0.01660
|
||||
roll_moment_delta_aileron_trim_scalar = -0.2
|
||||
yaw_moment_slip_angle = 0.18066
|
||||
yaw_moment_roll = 0.07470
|
||||
yaw_moment_yaw_damping = -2.49023
|
||||
yaw_moment_yaw_propwash = 0
|
||||
yaw_moment_delta_aileron = -0.00683
|
||||
yaw_moment_delta_rudder = 0.07128
|
||||
yaw_moment_delta_rudder_propwash = 0.075
|
||||
yaw_moment_delta_rudder_trim_scalar = -0.2
|
||||
compute_aero_center = 0
|
||||
aero_center_lift = -13.75
|
||||
lift_coef_aoa_table = -3.15:0, -2.36:0.36, -1.57:0, -0.349:-1.2, 0:-0.022, 0.0314:0.6082, 0.221:2.049, 0.244:1.15, 0.349:0.6, 0.436:0.5, 0.698:0.1, 1.963:-0.359, 2.356:-0.5, 3.15:0
|
||||
lift_coef_ground_effect_mach_table = 0.06:0.50, 0.227:0.80, 0.242:0.80, 0.3:1.0, 0.9:1.0
|
||||
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, 0.4:0.0054, 0.5:0.0056, 0.6:0.0059, 0.7:0.0062, 0.72:0.0062, 0.8:0.0063, 0.8:0.0063, 1:0.0337, 1.2:0.0337, 1.4:0.0337, 1.6:0.0337, 1.8:0.0337, 2.0:0.0337
|
||||
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:-2, -0.436:-0.626, -0.262:-0.434, 0:-0.146, 0.087:-0.05, 0.175:0.0466, 0.262:0.143, 0.314:0.2, 0.349:0.1, 0.436:0.15, 3.15:2
|
||||
pitch_moment_delta_elevator_aoa_table = -180:-1, -40:0.05, -20:0.455, -14:0.853, -7:1.007, 0:1, 7:0.839, 14:0.693, 20:0.381, 40:-0.08, 180:-1
|
||||
pitch_moment_horizontal_incidence_aoa_table = 0:1
|
||||
pitch_moment_daoa_aoa_table = 0:1
|
||||
pitch_moment_pitch_alpha_table = 0:1
|
||||
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
|
||||
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
|
||||
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 = -0.785:0.5, -0.524:0.85, -0.175:0.9, 0:1, 0.175:0.9, 0.524:0.85, 0.785:0.5 ; 0:1
|
||||
aileron_scaling_table = -0.785:1 ;0:1
|
||||
rudder_scaling_table = -0.785:0.5, -0.524:0.6, -0.175:0.9, 0:1, 0.175:0.9, 0.524:0.6, 0.785:0.5 ;0:1
|
||||
elevator_lift_coef=3
|
||||
rudder_lift_coef=2
|
||||
aileron_load_factor_effectiveness_table = 0:1
|
||||
lift_coef_at_drag_zero = 0.1
|
||||
lift_coef_at_drag_zero_flaps = 0.1
|
||||
|
||||
[FLIGHT_TUNING]
|
||||
modern_fm_only = 1
|
||||
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 = 5
|
||||
roll_stability = 1
|
||||
yaw_stability = 1
|
||||
pitch_gyro_stability = 1
|
||||
roll_gyro_stability = 1
|
||||
yaw_gyro_stability = 1
|
||||
empty_CG_deviation_limit=0
|
||||
elevator_trim_effectiveness = 1.5
|
||||
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
|
||||
wingflex_scalar = 2
|
||||
wingflex_offset = 0
|
||||
stall_coef_at_min_weight = 0.71
|
||||
ground_crosswind_effect_zero_speed=10
|
||||
ground_crosswind_effect_max_speed=150
|
||||
ground_high_speed_steeringwheel_static_friction_scalar=1.5
|
||||
ground_high_speed_otherwheel_static_friction_scalar=1.2
|
||||
|
||||
[REFERENCE SPEEDS]
|
||||
full_flaps_stall_speed = 115
|
||||
flaps_up_stall_speed = 149
|
||||
cruise_speed = 345
|
||||
cruise_mach = 0.85
|
||||
crossover_speed = 330
|
||||
max_mach = 0.9
|
||||
max_indicated_speed = 395
|
||||
max_flaps_extended = 170
|
||||
normal_operating_speed = 325
|
||||
airspeed_indicator_max = 562.5
|
||||
rotation_speed_min = 145
|
||||
climb_speed = 250
|
||||
cruise_alt = 41000
|
||||
takeoff_speed = 165
|
||||
spawn_cruise_altitude = 5000
|
||||
spawn_descent_altitude = 500
|
||||
best_angle_climb_speed = 0
|
||||
approach_speed = 0
|
||||
best_glide = 0
|
||||
max_gear_extended = 200
|
||||
|
||||
[INTERACTIVE POINTS]
|
||||
number_of_interactive_points = 3
|
||||
interactive_point.0 = 0.4, 44.15, -10.05, -0.567, 0, 0, 0, -88, 35, 0, 35, 0, 2, 33
|
||||
interactive_point.1 = 0.4, 75.65, 7.92, -0.567, 0, 0, 0, 75, 33, 2, 33, 2, 2, 33
|
||||
interactive_point.2 = 0.4, 33.3, 6.28, -7.18, 1, 0, 0, 90, 0, 0, 0, 0, 0, 0
|
||||
|
||||
[STALL PROTECTION]
|
||||
stall_protection = 1 ; Alpha Protection
|
||||
off_limit = 11.5 ; Alpha below which the Alpha Protection can be disabled (If also below off_yoke_limit)
|
||||
off_yoke_limit = 1 ; Yoke position (in Pct) below which the Alpha Protection can be disabled (If also below off_limit)
|
||||
on_limit = 14 ; Alpha above which the Alpha Protection timer starts
|
||||
on_goal = 10 ; The alpha that the Alpha Protection will attempt to reach when triggered
|
||||
timer_trigger = 1.0 ; Duration (in Sec) the alpha must be above on_limit before the Alpha Protection is triggered
|
||||
|
||||
;===================== FLAPS =====================
|
||||
|
||||
[FLAPS.0]
|
||||
type = 1
|
||||
system_type = 1
|
||||
span-outboard = 0.25
|
||||
extending-time = 22
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.1
|
||||
drag_scalar = 1.1
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 7
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 0, -1, 0
|
||||
flaps-position.2 = 15, 215, 0.25, 2, 0, 0, 0, 1
|
||||
flaps-position.3 = 20, 200, 0.26, 1.1, 0, 0, 0, 1
|
||||
flaps-position.4 = 24, 185, 0.28, 1.0, 0, 0, 0, 1
|
||||
flaps-position.5 = 28, 177, 0.3, 1.0, 1.5, 0, 0
|
||||
flaps-position.6 = 35, 160, 0.32, 1
|
||||
flaps-position.7 = 50, 150, 0.33, 1
|
||||
|
||||
|
||||
[FLAPS.1]
|
||||
type = 1
|
||||
system_type = 1
|
||||
span-outboard = 0.7
|
||||
extending-time = 23
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.1
|
||||
drag_scalar = 1.1
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 7
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 0, -1, 0
|
||||
flaps-position.2 = 15, 215, 0.25, 2, 0, 0, 0, 1
|
||||
flaps-position.3 = 20, 200, 0.26, 1.1, 0, 0, 0, 1
|
||||
flaps-position.4 = 24, 185, 0.28, 1.0, 0, 0, 0, 1
|
||||
flaps-position.5 = 28, 177, 0.3, 1.0, 1.5, 0, 0
|
||||
flaps-position.6 = 35, 160, 0.32, 1
|
||||
flaps-position.7 = 50, 150, 0.33, 1
|
||||
|
||||
|
||||
[FLAPS.2]
|
||||
type = 2
|
||||
system_type = 1
|
||||
span-outboard = 0.2
|
||||
extending-time = 8
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.5
|
||||
drag_scalar = 0.75
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 1
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 20, 215, 0.5, 0.5
|
||||
|
||||
[FLAPS.3]
|
||||
type = 2
|
||||
system_type = 1
|
||||
span-outboard = 0.7
|
||||
extending-time = 21
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.5
|
||||
drag_scalar = 0.75
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 1
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 20, 215, 0.5, 0.5
|
||||
@ -0,0 +1,406 @@
|
||||
//TFDi Designs MD-11 (PW4460) vRC1.7.0_PW 15MAY25
|
||||
|
||||
[VERSION]
|
||||
//KH Bump major
|
||||
major = 4
|
||||
minor = 1
|
||||
|
||||
[WEIGHT_AND_BALANCE]
|
||||
max_gross_weight = 630500
|
||||
empty_weight = 283975
|
||||
reference_datum_position = 0, 0, 0
|
||||
empty_weight_CG_position = -13.3, 0, 0
|
||||
CG_forward_limit = 0.12
|
||||
CG_aft_limit = 0.34
|
||||
empty_weight_pitch_MOI = 20897456
|
||||
empty_weight_roll_MOI = 6368555
|
||||
empty_weight_yaw_MOI = 40761191
|
||||
empty_weight_coupled_MOI = 0
|
||||
activate_mach_limit_based_on_cg = 0
|
||||
activate_cg_limit_based_on_mach = 0
|
||||
max_number_of_stations = 21
|
||||
//KH START Empty default
|
||||
station_load.0=0, 82.0, -2.0, 4.0, Pilot, 1
|
||||
station_load.1=0, 82.0, 2.0, 4.0, First Officer, 2
|
||||
station_load.2=0, 80.0, 3.3, 4.0, Engineer, 0
|
||||
station_load.3=0, 66.0, 0.0, 4.0, Cabin crew 1, 0
|
||||
station_load.4=0, 45.0, -5.0, 4.0, Business 1 L, 0
|
||||
station_load.5=0, 45.0, 0.0, 4.0, Business 1 C, 0
|
||||
station_load.6=0, 45.0, 5.0, 4.0, Business 1 R, 0
|
||||
station_load.7=0, 25.0, -5.0, 4.0, Business 2 L, 0
|
||||
station_load.8=0, 25.0, 0.0, 4.0, Business 2 C, 0
|
||||
station_load.9=0, 25.0, 5.0, 4.0, Business 2 R, 0
|
||||
station_load.10=0, -20.0, -5.0, 4.0, Economy 3 L, 0
|
||||
station_load.11=0, -20.0, 0.0, 4.0, Economy 3 C, 0
|
||||
station_load.12=0, -20.0, 5.0, 4.0, Economy 3 R, 0
|
||||
station_load.13=0, -50.0, -5.0, 4.0, Economy 4 L, 0
|
||||
station_load.14=0, -50.0, 0.0, 4.0, Economy 4 C, 0
|
||||
station_load.15=0, -50.0, 5.0, 4.0, Economy 4 R, 0
|
||||
station_load.16=0, -55.0, 0.0, 4.0, Cabin crew 2, 0
|
||||
station_load.17=0, 30.0, 0.0, -4.5, Forward cargo, 0
|
||||
station_load.18=0, -30.0, 0.0, -4.5, Rear cargo, 0
|
||||
station_load.19=0, 5.0, -2.0, -4.5, Left aux tank, 0
|
||||
station_load.20=0, 5.0, 2.0, -4.5, Right aux tank, 0
|
||||
//KH END
|
||||
|
||||
[CONTACT_POINTS]
|
||||
static_pitch = 0
|
||||
static_cg_height = 16.4
|
||||
gear_system_type = 1
|
||||
tailwheel_lock = 0
|
||||
max_number_of_points = 16
|
||||
gear_locked_on_ground = 0
|
||||
gear_locked_above_speed = -1
|
||||
max_speed_full_steering = 25
|
||||
min_available_steering_angle_pct = 0.2
|
||||
max_speed_decreasing_steering = 45
|
||||
max_speed_full_steering_castering = 20
|
||||
max_speed_decreasing_steering_castering = 35
|
||||
emergency_extension_type = 2
|
||||
hyd_need_power_to_function= 0
|
||||
min_castering_angle = 0.05236
|
||||
max_castering_angle = 1.32645
|
||||
allow_stopped_steering = 1
|
||||
point.0 = 1, 64.22, 0.00, -17.31, 1500, 0, 1.67, 70, 1.15, 1.183, 0.9, 49, 50, 0, 200, 250, 8
|
||||
point.1 = 1, -19.00, -17.15, -18.02, 2000, 1, 2.25, 0, 1.60, 1.116, 0.9, 51, 52, 2, 200, 250, 8
|
||||
point.2 = 1, -19.00, 17.15, -18.02, 2000, 2, 2.25, 0, 1.60, 1.116, 0.9, 53, 54, 3, 200, 250, 8
|
||||
point.3 = 1, -19.00, 0.00, -18.02, 2000, 2, 2.25, 0, 1.60, 1.116, 0.9, 55, 56, 3, 200, 250, 8
|
||||
point.4 = 2, 93.0, 0.0, 0.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
|
||||
point.5 = 2, -48, -82.5, 0.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 5, 0, 0, 1
|
||||
point.6 = 2, -48, 82.5, 0.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 6, 0, 0, 1
|
||||
point.7 = 2, 60, 0.0, -9.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
|
||||
point.8 = 2, 60, 0.0, 11.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
|
||||
point.9 = 2, 16.0, -28.00, -13.00, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.10 = 2, 16.0, 28.00, -13.00, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.11 = 2, -110.0, 0.00, 14.20, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.12 = 2, -96.5, 0.0, 42.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.13 = 2, -94.5, -30.0, 8.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.14 = 2, -94.5, 30.0, 8.05, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 4, 0, 0, 1
|
||||
point.15 = 2, -52.0, 0.0, -9.0, 787, 0, 0.0, 0, 0.00, 0.0, 0.0, 0.0, 0.0, 9, 0, 0, 1
|
||||
|
||||
[FUEL]
|
||||
LeftMain = -20.00, -38.00, -1.0, 8938, 10.00
|
||||
RightMain = -20.00, 38.00, -1.0, 8938, 10.00
|
||||
Center1 = 10.00, 0.00, -3.00, 13000.00, 10.00
|
||||
Center2 = 0.00, 0.00, -1.00, 1642.00, 10.00
|
||||
Center3 = 0.00, 0.00, -5.00, 1958.00, 11.00
|
||||
LeftTip = -39.00, -74.00, 0.00, 884.00, 10.00
|
||||
RightTip = -39.00, 74.00, 0.00, 884.00, 10.00
|
||||
External1 = -70.00, 0.00, -3.00, 2371.00, 10.00
|
||||
//KH From 5.00, -2.00, -3.00, 0.00, 10.00
|
||||
LeftAux = 5.00, -2.00, -3.00, 1917.00, 10.00
|
||||
//KH From 5.00, 2.00, -3.00, 0.00, 10.0
|
||||
RightAux = 5.00, 2.00, -3.00, 1917.00, 10.00
|
||||
fuel_type = 2
|
||||
number_of_tank_selectors = 3
|
||||
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_tank_selector.2 = 1
|
||||
default_fuel_tank_selector.3 = 1
|
||||
|
||||
[AIRPLANE_GEOMETRY]
|
||||
wing_area = 3648
|
||||
wing_span = 170.5
|
||||
wing_root_chord = 34.68
|
||||
wing_camber = 1
|
||||
wing_thickness_ratio = 0.04
|
||||
wing_dihedral = 2.2
|
||||
wing_incidence = 1.5
|
||||
wing_twist = -0.5
|
||||
oswald_efficiency_factor = 0.72
|
||||
wing_winglets_flag = 1
|
||||
wing_sweep = 38
|
||||
wing_pos_apex_lon = 1
|
||||
wing_pos_apex_vert = -2.75
|
||||
htail_area = 920
|
||||
htail_span = 59.5
|
||||
htail_pos_lon = -88
|
||||
htail_pos_vert = 5.0
|
||||
htail_incidence = 0.8
|
||||
htail_sweep = 36.5
|
||||
htail_thickness_ratio = 0.02
|
||||
vtail_area = 760
|
||||
vtail_span = 28.1
|
||||
vtail_sweep = 43
|
||||
vtail_pos_lon = -79.5
|
||||
vtail_pos_vert = 28
|
||||
vtail_thickness_ratio = 0.03
|
||||
fuselage_length = 200.92
|
||||
fuselage_diameter = 19.75
|
||||
fuselage_center_pos = 10, 0, 1.0
|
||||
elevator_area = 327.0
|
||||
aileron_area = 225.0
|
||||
rudder_area = 190.0
|
||||
elevator_up_limit = 25
|
||||
elevator_down_limit = 15
|
||||
aileron_up_limit = 25
|
||||
aileron_down_limit = 15
|
||||
rudder_limit = 23
|
||||
rudder_trim_limit = 20
|
||||
elevator_trim_limit = 30
|
||||
spoiler_limit = 60
|
||||
spoilerons_available = 1
|
||||
aileron_to_spoileron_gain = 3
|
||||
min_ailerons_for_spoilerons = 10
|
||||
min_flaps_for_spoilerons = 0
|
||||
spoiler_extension_time = 2.0
|
||||
spoiler_handle_available = 1
|
||||
auto_spoiler_available = 1
|
||||
auto_spoiler_auto_retracts = 0
|
||||
auto_spoiler_min_speed = 72
|
||||
positive_g_limit_flaps_up = 5.0
|
||||
positive_g_limit_flaps_down = 4.0
|
||||
negative_g_limit_flaps_up = -4.0
|
||||
negative_g_limit_flaps_down = -3.0
|
||||
load_safety_factor = 1.5
|
||||
elevator_trim_neutral = -1
|
||||
aileron_to_rudder_scale = 0
|
||||
flap_to_aileron_scale = 0
|
||||
fly_by_wire = 0
|
||||
elevator_elasticity_table = 0:0.7, 87:0.3, 210:0.5, 315:0.5
|
||||
aileron_elasticity_table = 0:1, 300:0.7, 600:0.6, 1500:0.4
|
||||
rudder_elasticity_table = 0:1, 300:1, 800:1, 1000:0.7
|
||||
elevator_trim_elasticity_table = 0:0.0, 87:0.40, 240:0.60, 295:1.00, 315:1.00
|
||||
|
||||
[AERODYNAMICS]
|
||||
lift_coef_pitch_rate = -8.09375
|
||||
lift_coef_daoa = 2.68359
|
||||
lift_coef_delta_elevator = -0.28906
|
||||
lift_coef_horizontal_incidence = 0.91357
|
||||
lift_coef_flaps = 1
|
||||
lift_coef_spoilers = 0
|
||||
drag_coef_zero_lift = 0.02539
|
||||
drag_coef_flaps = 0.1889
|
||||
drag_coef_gear = 0.0549
|
||||
drag_coef_spoilers = 0.05207
|
||||
side_force_slip_angle = -0.77392
|
||||
side_force_roll_rate = 0.15478
|
||||
side_force_yaw_rate = 0
|
||||
side_force_delta_rudder = -0.14746
|
||||
pitch_moment_horizontal_incidence = 4.24755
|
||||
pitch_moment_delta_elevator = -2.37011
|
||||
pitch_moment_delta_trim = 0
|
||||
pitch_moment_pitch_damping = -214.1455
|
||||
pitch_moment_aoa_0 = 0.11621
|
||||
pitch_moment_daoa = 8.87255
|
||||
pitch_moment_flaps = 0.0105
|
||||
pitch_moment_gear = 0.0171
|
||||
pitch_moment_spoilers = 0
|
||||
pitch_moment_delta_elevator_propwash = -2.37011
|
||||
pitch_moment_pitch_propwash = -214.1455
|
||||
roll_moment_slip_angle = 0.26855
|
||||
roll_moment_roll_damping = -3.40869
|
||||
roll_moment_yaw_rate = -0.27197
|
||||
roll_moment_spoilers = 0.07
|
||||
roll_moment_delta_aileron = -0.34521
|
||||
roll_moment_delta_rudder = 0.01660
|
||||
roll_moment_delta_aileron_trim_scalar = -0.2
|
||||
yaw_moment_slip_angle = 0.18066
|
||||
yaw_moment_roll = 0.07470
|
||||
yaw_moment_yaw_damping = -2.49023
|
||||
yaw_moment_yaw_propwash = 0
|
||||
yaw_moment_delta_aileron = -0.00683
|
||||
yaw_moment_delta_rudder = 0.07128
|
||||
yaw_moment_delta_rudder_propwash = 0.075
|
||||
yaw_moment_delta_rudder_trim_scalar = -0.2
|
||||
compute_aero_center = 0
|
||||
aero_center_lift = -13.75
|
||||
lift_coef_aoa_table = -3.15:0, -2.36:0.36, -1.57:0, -0.349:-1.2, 0:-0.022, 0.0314:0.6082, 0.221:2.049, 0.244:1.15, 0.349:0.6, 0.436:0.5, 0.698:0.1, 1.963:-0.359, 2.356:-0.5, 3.15:0
|
||||
lift_coef_ground_effect_mach_table = 0.06:0.50, 0.227:0.80, 0.242:0.80, 0.3:1.0, 0.9:1.0
|
||||
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, 0.4:0.0054, 0.5:0.0056, 0.6:0.0059, 0.7:0.0062, 0.72:0.0062, 0.8:0.0063, 0.8:0.0063, 1:0.0337, 1.2:0.0337, 1.4:0.0337, 1.6:0.0337, 1.8:0.0337, 2.0:0.0337
|
||||
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:-2, -0.436:-0.626, -0.262:-0.434, 0:-0.146, 0.087:-0.05, 0.175:0.0466, 0.262:0.143, 0.314:0.2, 0.349:0.1, 0.436:0.15, 3.15:2
|
||||
pitch_moment_delta_elevator_aoa_table = -180:-1, -40:0.05, -20:0.455, -14:0.853, -7:1.007, 0:1, 7:0.839, 14:0.693, 20:0.381, 40:-0.08, 180:-1
|
||||
pitch_moment_horizontal_incidence_aoa_table = 0:1
|
||||
pitch_moment_daoa_aoa_table = 0:1
|
||||
pitch_moment_pitch_alpha_table = 0:1
|
||||
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
|
||||
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
|
||||
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 = -0.785:0.5, -0.524:0.85, -0.175:0.9, 0:1, 0.175:0.9, 0.524:0.85, 0.785:0.5 ; 0:1
|
||||
aileron_scaling_table = -0.785:1 ;0:1
|
||||
rudder_scaling_table = -0.785:0.5, -0.524:0.6, -0.175:0.9, 0:1, 0.175:0.9, 0.524:0.6, 0.785:0.5 ;0:1
|
||||
elevator_lift_coef=3
|
||||
rudder_lift_coef=2
|
||||
aileron_load_factor_effectiveness_table = 0:1
|
||||
lift_coef_at_drag_zero = 0.1
|
||||
lift_coef_at_drag_zero_flaps = 0.1
|
||||
|
||||
[FLIGHT_TUNING]
|
||||
modern_fm_only = 1
|
||||
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 = 5
|
||||
roll_stability = 1
|
||||
yaw_stability = 1
|
||||
pitch_gyro_stability = 1
|
||||
roll_gyro_stability = 1
|
||||
yaw_gyro_stability = 1
|
||||
empty_CG_deviation_limit=0
|
||||
elevator_trim_effectiveness = 1.5
|
||||
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
|
||||
wingflex_scalar = 2
|
||||
wingflex_offset = 0
|
||||
stall_coef_at_min_weight = 0.71
|
||||
ground_crosswind_effect_zero_speed=10
|
||||
ground_crosswind_effect_max_speed=150
|
||||
ground_high_speed_steeringwheel_static_friction_scalar=1.5
|
||||
ground_high_speed_otherwheel_static_friction_scalar=1.2
|
||||
|
||||
[REFERENCE SPEEDS]
|
||||
full_flaps_stall_speed = 115
|
||||
flaps_up_stall_speed = 149
|
||||
cruise_speed = 345
|
||||
cruise_mach = 0.85
|
||||
crossover_speed = 330
|
||||
max_mach = 0.9
|
||||
max_indicated_speed = 395
|
||||
max_flaps_extended = 170
|
||||
normal_operating_speed = 325
|
||||
airspeed_indicator_max = 562.5
|
||||
rotation_speed_min = 145
|
||||
climb_speed = 250
|
||||
cruise_alt = 41000
|
||||
takeoff_speed = 165
|
||||
spawn_cruise_altitude = 5000
|
||||
spawn_descent_altitude = 500
|
||||
best_angle_climb_speed = 0
|
||||
approach_speed = 0
|
||||
best_glide = 0
|
||||
max_gear_extended = 200
|
||||
|
||||
[INTERACTIVE POINTS]
|
||||
number_of_interactive_points = 3
|
||||
interactive_point.0 = 0.4, 44.15, -10.05, -0.567, 0, 0, 0, -88, 35, 0, 35, 0, 2, 33
|
||||
interactive_point.1 = 0.4, 75.65, 7.92, -0.567, 0, 0, 0, 75, 33, 2, 33, 2, 2, 33
|
||||
interactive_point.2 = 0.4, 33.3, 6.28, -7.18, 1, 0, 0, 90, 0, 0, 0, 0, 0, 0
|
||||
|
||||
[STALL PROTECTION]
|
||||
stall_protection = 1 ; Alpha Protection
|
||||
off_limit = 11.5 ; Alpha below which the Alpha Protection can be disabled (If also below off_yoke_limit)
|
||||
off_yoke_limit = 1 ; Yoke position (in Pct) below which the Alpha Protection can be disabled (If also below off_limit)
|
||||
on_limit = 14 ; Alpha above which the Alpha Protection timer starts
|
||||
on_goal = 10 ; The alpha that the Alpha Protection will attempt to reach when triggered
|
||||
timer_trigger = 1.0 ; Duration (in Sec) the alpha must be above on_limit before the Alpha Protection is triggered
|
||||
|
||||
;===================== FLAPS =====================
|
||||
|
||||
[FLAPS.0]
|
||||
type = 1
|
||||
system_type = 1
|
||||
span-outboard = 0.25
|
||||
extending-time = 22
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.1
|
||||
drag_scalar = 1.1
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 7
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 0, -1, 0
|
||||
flaps-position.2 = 15, 215, 0.25, 2, 0, 0, 0, 1
|
||||
flaps-position.3 = 20, 200, 0.26, 1.1, 0, 0, 0, 1
|
||||
flaps-position.4 = 24, 185, 0.28, 1.0, 0, 0, 0, 1
|
||||
flaps-position.5 = 28, 177, 0.3, 1.0, 1.5, 0, 0
|
||||
flaps-position.6 = 35, 160, 0.32, 1
|
||||
flaps-position.7 = 50, 150, 0.33, 1
|
||||
|
||||
[FLAPS.1]
|
||||
type = 1
|
||||
system_type = 1
|
||||
span-outboard = 0.7
|
||||
extending-time = 23
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.1
|
||||
drag_scalar = 1.1
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 7
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 0, -1, 0
|
||||
flaps-position.2 = 15, 215, 0.25, 2, 0, 0, 0, 1
|
||||
flaps-position.3 = 20, 200, 0.26, 1.1, 0, 0, 0, 1
|
||||
flaps-position.4 = 24, 185, 0.28, 1.0, 0, 0, 0, 1
|
||||
flaps-position.5 = 28, 177, 0.3, 1.0, 1.5, 0, 0
|
||||
flaps-position.6 = 35, 160, 0.32, 1
|
||||
flaps-position.7 = 50, 150, 0.33, 1
|
||||
|
||||
[FLAPS.2]
|
||||
type = 2
|
||||
system_type = 1
|
||||
span-outboard = 0.2
|
||||
extending-time = 8
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.5
|
||||
drag_scalar = 0.75
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 1
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 20, 215, 0.5, 0.5
|
||||
|
||||
[FLAPS.3]
|
||||
type = 2
|
||||
system_type = 1
|
||||
span-outboard = 0.7
|
||||
extending-time = 21
|
||||
damaging-speed = 250
|
||||
blowout-speed = 300
|
||||
maneuvering_flaps = 0
|
||||
lift_scalar = 0.5
|
||||
drag_scalar = 0.75
|
||||
pitch_scalar = 1
|
||||
max_on_ground_position = 1
|
||||
flaps-position.0 = 0, -1, 0
|
||||
flaps-position.1 = 20, 215, 0.5, 0.5
|
||||
Loading…
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Reference in New Issue
Block a user