- Messages
- 10,158
- Country
I have waited EONS for this!!! Lovely... The AIR file Section 1101 in a config file, including tables!
Sample from the Aerodynamics section of the sample plane's 'flight_model.cfg' file.
[AERODYNAMICS]
lift_coef_pitch_rate = -3.899902 ; The change in lift per change in pitch rate
lift_coef_daoa = 1.699707 ; lift per change in angle of attack rate
lift_coef_delta_elevator = -0.372559 ; The change in lift per change in elevator deflection
lift_coef_horizontal_incidence = -0.567871 ; The change in lift per change in horizontal incidence angle
lift_coef_flaps = 0.44 ; Change in lift due to flaps
lift_coef_spoilers = 0 ; Change in lift due to spoilers
drag_coef_zero_lift = 0.029785 ; The zero lift drag polar
drag_coef_flaps = 0.107422
drag_coef_gear = 0.006836
drag_coef_spoilers = 0
side_force_slip_angle = -0.399902 ; (yaw angle) The change in side force per change in side slip angle
side_force_roll_rate = 0.04248 ; (roll velocity) The change in side force per change in roll rate
side_force_yaw_rate = 0.04834 ; (yaw velocity) The change in side force per change in yaw rate
side_force_delta_rudder = -0.200195 ; The change in side force per change in rudder deflection
pitch_moment_horizontal_incidence = 0 ; The change in pitch moment per change in horizontal incidence angle
pitch_moment_delta_elevator = -0.78125 ; The change in pitch moment per change in elevator deflection
pitch_moment_delta_trim = -0.48 ; The change in pitch moment per change in trim
pitch_moment_pitch_damping = -14.648438 ; The change in pitch moment per change in pitch rate(PRIMARY PITCH STABILITY FACTOR). deg/s
pitch_moment_aoa_0 = -0.13 ; Pitch moment at zero angle - of - attack
pitch_moment_daoa = 5.859375 ; The change in pitch moment per change in angle of attack
pitch_moment_flaps = -0.04 ; The pitch moment due to flaps
pitch_moment_gear = 0 ; The pitch moment due to gear
pitch_moment_spoilers = 0 ; The pitch moment due to spoilers
pitch_moment_delta_elevator_propwash = -0.0512
pitch_moment_pitch_propwash = 0
roll_moment_slip_angle = 0.073242 ; The change in roll moment per sideslip angle(DIHEDRAL EFFECT)
roll_moment_roll_damping = -0.46
roll_moment_yaw_rate = 0
roll_moment_spoilers = 0 ; The change in roll moment due to spoilers
roll_moment_delta_aileron = -0.227539 ; (control)The change in roll moment per change in aileron deflection
roll_moment_delta_rudder = 0.014648 ; (control)The change in roll moment per change rudder deflection
roll_moment_delta_aileron_trim_scalar = 0 ; Change in roll moment due to aileron trim
yaw_moment_slip_angle = 0.068359 ; The change in yaw moment per change sideslip angle(WEATHER VANING EFFECT)
yaw_moment_roll = 0.05957 ; (adverse yaw) The change in yaw moment per change in roll rate deg/s
yaw_moment_yaw_damping = -0.180664 ; (damping)The change in yaw moment per change in yaw rate(PRIMARY YAW STABILITY FACTOR deg/s)
yaw_moment_yaw_propwash = 0 ; (damping)
yaw_moment_delta_aileron = -0.014648 ; (adverse yaw) The change in yaw moment per change aileron deflection
yaw_moment_delta_rudder = 0.054688 ; (control)The change in yaw moment per change in rudder deflection PRIMARY YAW POWER FACTOR
yaw_moment_delta_rudder_propwash = 0 ; (control)
yaw_moment_delta_rudder_trim_scalar = 0.05236 ; Change in yaw moment due to rudder trim
compute_aero_center = 0
aero_center_lift = -0.2 ; Init to center
lift_coef_aoa_table = -3.142:0, -2.356:0.5, -1.571:0, -0.334:-1.078, -0.072:0, 0:0.358, 0.227:1.478, 0.262:1.5013, 0.297:1.478, 0.332:1.078, 1.571:0, 2.356:-0.5, 3.142:0
lift_coef_ground_effect_mach_table = 0.054:1.25, 0.1:1.16, 0.2:1.0961, 0.3:1.06, 0.4:1.04, 0.5:1.03, 0.6:1.0242, 0.7:1.0213, 0.8:1.0161, 0.9:1.01, 1:1
lift_coef_mach_table = 0:1, 0.2:1, 0.4:1, 0.6:1, 0.8:1, 1:1, 1.2:1, 1.4:1, 1.6:1, 1.8:1, 2:1, 2.2:1, 2.4:1, 2.6:1, 2.8:1, 3:1, 3.2:1
lift_coef_delta_elevator_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
lift_coef_daoa_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
lift_coef_pitch_rate_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
lift_coef_horizontal_incidence_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
drag_coef_zero_lift_mach_tab = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0.007328, 1:0.077675, 1.2:0.057157, 1.4:0.057157, 1.6:0.057157, 1.8:0.057157, 2:0.057157, 2.2:0.057157, 2.4:0.057157, 2.6:0.057157, 2.8:0.057157, 3:0.057157, 3.2:0.057157
side_force_slip_angle_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
side_force_delta_rudder_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
side_force_yaw_rate_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
side_force_roll_rate_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
pitch_moment_aoa_table = -3.142:0, -0.524:-0.436, -0.349:-0.436, -0.279:-0.218, -0.262:-0.182, -0.244:-0.151, 0:0, 0.244:0.151, 0.262:0.182, 0.279:0.218, 0.349:0.436, 0.524:0.436, 3.142:0
pitch_moment_delta_elevator_aoa_table = 0:1 ; AoA(alpha) is given in DEGREES
pitch_moment_horizontal_incidence_aoa_table = 0:1 ; AoA(alpha) is given in DEGREES
pitch_moment_daoa_aoa_table = 0:1 ; AoA(alpha) is given in DEGREES
pitch_moment_pitch_alpha_table = 0:1 ; AoA(alpha) is given in DEGREES
pitch_moment_delta_elevator_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
pitch_moment_daoa_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
pitch_moment_pitch_rate_mach_table = 0:0, 0.2:-2.442599, 0.4:-4.885198, 0.6:-7.327797, 0.8:-9.770396, 1:-9.770396, 1.2:-9.770396, 1.4:-9.770396, 1.6:-9.770396, 1.8:-9.770396, 2:-9.770396, 2.2:-9.770396, 2.4:-9.770396, 2.6:-9.770396, 2.8:-9.770396, 3:-9.770396, 3.2:-9.770396
pitch_moment_horizontal_incidence_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
pitch_moment_aoa_0_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
roll_moment_aoa_table = 0:0 ; Cl (roll moment coef) versus AoA
roll_moment_slip_angle_aoa_table = -180:3, -20:3.2, -15:2, -10:1, 0:1, 10:1, 15:2, 20:3, 180:3
roll_moment_roll_rate_aoa_table = -180:1, -90:1, -18:1, -10:1, 0:1, 10:1, 18:1, 90:1, 180:1
roll_moment_delta_aileron_aoa_table = 0:1
roll_moment_slip_angle_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
roll_moment_delta_rudder_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
roll_moment_delta_aileron_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
roll_moment_yaw_rate_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
roll_moment_roll_rate_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
yaw_moment_aoa_table = 0:0 ; Cn (yaw moment coef) versus AoA
yaw_moment_slip_angle_aoa_table = -180:1, -90:0.4, -18:0.2, -10:0.7, 0:1, 10:0.7, 18:0.2, 90:0.4, 180:1
yaw_moment_yaw_rate_aoa_table = -180:0.5, -90:0.5, -16:0.5, -10:1, 0:1, 10:1, 16:0.5, 90:0.5, 180:0.5
yaw_moment_delta_rudder_aoa_table = 0:1
yaw_moment_slip_angle_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
yaw_moment_delta_rudder_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
yaw_moment_delta_aileron_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
yaw_moment_yaw_rate_mach_table = 0:0, 0.2:-0.024426, 0.4:-0.061065, 0.6:-0.12213, 0.8:-0.12213, 1:-0.12213, 1.2:-0.12213, 1.4:-0.12213, 1.6:-0.12213, 1.8:-0.12213, 2:-0.12213, 2.2:-0.12213, 2.4:-0.12213, 2.6:-0.12213, 2.8:-0.12213, 3:-0.12213, 3.2:-0.12213
yaw_moment_roll_rate_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
elevator_scaling_table = -0.524:1, -0.349:1, -0.175:1, 0:1, 0.175:1, 0.349:1, 0.524:1 ; scales control based on its deflection
aileron_scaling_table = -0.524:1, -0.349:1, -0.175:0.5, 0:0.3, 0.175:0.5, 0.349:1, 0.524:1 ; scales control based on its deflection
rudder_scaling_table = -0.785:1, -0.524:1, -0.175:1, 0:1, 0.175:1, 0.524:1, 0.785:1 ; scales control based on its deflection
aileron_load_factor_effectiveness_table = 0:1 ; scaling of roll_moment_delta_aileron versus gravity forces, G effects on aileron effectiveness, acts on roll_moment_delta_aileron
Sample from the Aerodynamics section of the sample plane's 'flight_model.cfg' file.
[AERODYNAMICS]
lift_coef_pitch_rate = -3.899902 ; The change in lift per change in pitch rate
lift_coef_daoa = 1.699707 ; lift per change in angle of attack rate
lift_coef_delta_elevator = -0.372559 ; The change in lift per change in elevator deflection
lift_coef_horizontal_incidence = -0.567871 ; The change in lift per change in horizontal incidence angle
lift_coef_flaps = 0.44 ; Change in lift due to flaps
lift_coef_spoilers = 0 ; Change in lift due to spoilers
drag_coef_zero_lift = 0.029785 ; The zero lift drag polar
drag_coef_flaps = 0.107422
drag_coef_gear = 0.006836
drag_coef_spoilers = 0
side_force_slip_angle = -0.399902 ; (yaw angle) The change in side force per change in side slip angle
side_force_roll_rate = 0.04248 ; (roll velocity) The change in side force per change in roll rate
side_force_yaw_rate = 0.04834 ; (yaw velocity) The change in side force per change in yaw rate
side_force_delta_rudder = -0.200195 ; The change in side force per change in rudder deflection
pitch_moment_horizontal_incidence = 0 ; The change in pitch moment per change in horizontal incidence angle
pitch_moment_delta_elevator = -0.78125 ; The change in pitch moment per change in elevator deflection
pitch_moment_delta_trim = -0.48 ; The change in pitch moment per change in trim
pitch_moment_pitch_damping = -14.648438 ; The change in pitch moment per change in pitch rate(PRIMARY PITCH STABILITY FACTOR). deg/s
pitch_moment_aoa_0 = -0.13 ; Pitch moment at zero angle - of - attack
pitch_moment_daoa = 5.859375 ; The change in pitch moment per change in angle of attack
pitch_moment_flaps = -0.04 ; The pitch moment due to flaps
pitch_moment_gear = 0 ; The pitch moment due to gear
pitch_moment_spoilers = 0 ; The pitch moment due to spoilers
pitch_moment_delta_elevator_propwash = -0.0512
pitch_moment_pitch_propwash = 0
roll_moment_slip_angle = 0.073242 ; The change in roll moment per sideslip angle(DIHEDRAL EFFECT)
roll_moment_roll_damping = -0.46
roll_moment_yaw_rate = 0
roll_moment_spoilers = 0 ; The change in roll moment due to spoilers
roll_moment_delta_aileron = -0.227539 ; (control)The change in roll moment per change in aileron deflection
roll_moment_delta_rudder = 0.014648 ; (control)The change in roll moment per change rudder deflection
roll_moment_delta_aileron_trim_scalar = 0 ; Change in roll moment due to aileron trim
yaw_moment_slip_angle = 0.068359 ; The change in yaw moment per change sideslip angle(WEATHER VANING EFFECT)
yaw_moment_roll = 0.05957 ; (adverse yaw) The change in yaw moment per change in roll rate deg/s
yaw_moment_yaw_damping = -0.180664 ; (damping)The change in yaw moment per change in yaw rate(PRIMARY YAW STABILITY FACTOR deg/s)
yaw_moment_yaw_propwash = 0 ; (damping)
yaw_moment_delta_aileron = -0.014648 ; (adverse yaw) The change in yaw moment per change aileron deflection
yaw_moment_delta_rudder = 0.054688 ; (control)The change in yaw moment per change in rudder deflection PRIMARY YAW POWER FACTOR
yaw_moment_delta_rudder_propwash = 0 ; (control)
yaw_moment_delta_rudder_trim_scalar = 0.05236 ; Change in yaw moment due to rudder trim
compute_aero_center = 0
aero_center_lift = -0.2 ; Init to center
lift_coef_aoa_table = -3.142:0, -2.356:0.5, -1.571:0, -0.334:-1.078, -0.072:0, 0:0.358, 0.227:1.478, 0.262:1.5013, 0.297:1.478, 0.332:1.078, 1.571:0, 2.356:-0.5, 3.142:0
lift_coef_ground_effect_mach_table = 0.054:1.25, 0.1:1.16, 0.2:1.0961, 0.3:1.06, 0.4:1.04, 0.5:1.03, 0.6:1.0242, 0.7:1.0213, 0.8:1.0161, 0.9:1.01, 1:1
lift_coef_mach_table = 0:1, 0.2:1, 0.4:1, 0.6:1, 0.8:1, 1:1, 1.2:1, 1.4:1, 1.6:1, 1.8:1, 2:1, 2.2:1, 2.4:1, 2.6:1, 2.8:1, 3:1, 3.2:1
lift_coef_delta_elevator_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
lift_coef_daoa_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
lift_coef_pitch_rate_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
lift_coef_horizontal_incidence_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
drag_coef_zero_lift_mach_tab = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0.007328, 1:0.077675, 1.2:0.057157, 1.4:0.057157, 1.6:0.057157, 1.8:0.057157, 2:0.057157, 2.2:0.057157, 2.4:0.057157, 2.6:0.057157, 2.8:0.057157, 3:0.057157, 3.2:0.057157
side_force_slip_angle_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
side_force_delta_rudder_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
side_force_yaw_rate_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
side_force_roll_rate_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
pitch_moment_aoa_table = -3.142:0, -0.524:-0.436, -0.349:-0.436, -0.279:-0.218, -0.262:-0.182, -0.244:-0.151, 0:0, 0.244:0.151, 0.262:0.182, 0.279:0.218, 0.349:0.436, 0.524:0.436, 3.142:0
pitch_moment_delta_elevator_aoa_table = 0:1 ; AoA(alpha) is given in DEGREES
pitch_moment_horizontal_incidence_aoa_table = 0:1 ; AoA(alpha) is given in DEGREES
pitch_moment_daoa_aoa_table = 0:1 ; AoA(alpha) is given in DEGREES
pitch_moment_pitch_alpha_table = 0:1 ; AoA(alpha) is given in DEGREES
pitch_moment_delta_elevator_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
pitch_moment_daoa_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
pitch_moment_pitch_rate_mach_table = 0:0, 0.2:-2.442599, 0.4:-4.885198, 0.6:-7.327797, 0.8:-9.770396, 1:-9.770396, 1.2:-9.770396, 1.4:-9.770396, 1.6:-9.770396, 1.8:-9.770396, 2:-9.770396, 2.2:-9.770396, 2.4:-9.770396, 2.6:-9.770396, 2.8:-9.770396, 3:-9.770396, 3.2:-9.770396
pitch_moment_horizontal_incidence_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
pitch_moment_aoa_0_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
roll_moment_aoa_table = 0:0 ; Cl (roll moment coef) versus AoA
roll_moment_slip_angle_aoa_table = -180:3, -20:3.2, -15:2, -10:1, 0:1, 10:1, 15:2, 20:3, 180:3
roll_moment_roll_rate_aoa_table = -180:1, -90:1, -18:1, -10:1, 0:1, 10:1, 18:1, 90:1, 180:1
roll_moment_delta_aileron_aoa_table = 0:1
roll_moment_slip_angle_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
roll_moment_delta_rudder_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
roll_moment_delta_aileron_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
roll_moment_yaw_rate_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
roll_moment_roll_rate_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
yaw_moment_aoa_table = 0:0 ; Cn (yaw moment coef) versus AoA
yaw_moment_slip_angle_aoa_table = -180:1, -90:0.4, -18:0.2, -10:0.7, 0:1, 10:0.7, 18:0.2, 90:0.4, 180:1
yaw_moment_yaw_rate_aoa_table = -180:0.5, -90:0.5, -16:0.5, -10:1, 0:1, 10:1, 16:0.5, 90:0.5, 180:0.5
yaw_moment_delta_rudder_aoa_table = 0:1
yaw_moment_slip_angle_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
yaw_moment_delta_rudder_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
yaw_moment_delta_aileron_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
yaw_moment_yaw_rate_mach_table = 0:0, 0.2:-0.024426, 0.4:-0.061065, 0.6:-0.12213, 0.8:-0.12213, 1:-0.12213, 1.2:-0.12213, 1.4:-0.12213, 1.6:-0.12213, 1.8:-0.12213, 2:-0.12213, 2.2:-0.12213, 2.4:-0.12213, 2.6:-0.12213, 2.8:-0.12213, 3:-0.12213, 3.2:-0.12213
yaw_moment_roll_rate_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0, 1:0, 1.2:0, 1.4:0, 1.6:0, 1.8:0, 2:0, 2.2:0, 2.4:0, 2.6:0, 2.8:0, 3:0, 3.2:0
elevator_scaling_table = -0.524:1, -0.349:1, -0.175:1, 0:1, 0.175:1, 0.349:1, 0.524:1 ; scales control based on its deflection
aileron_scaling_table = -0.524:1, -0.349:1, -0.175:0.5, 0:0.3, 0.175:0.5, 0.349:1, 0.524:1 ; scales control based on its deflection
rudder_scaling_table = -0.785:1, -0.524:1, -0.175:1, 0:1, 0.175:1, 0.524:1, 0.785:1 ; scales control based on its deflection
aileron_load_factor_effectiveness_table = 0:1 ; scaling of roll_moment_delta_aileron versus gravity forces, G effects on aileron effectiveness, acts on roll_moment_delta_aileron
