I don't normally post my mods since the FS community generally has very high expectations and preferences vary. But this scenario is an exception because the product's quality is inferior, and the updated aerodynamic settings in V1.3 is flawed and not thoroughly tested.

Having said that, I do like elements of the V1.3 updates like the sound, pitot heat and yaw damper so instead of going back to V1.2, I decided to mod. This performance mod specifically addresses the climbing issues above FL20.  It is NOT perfect, as the climb at that level still exhibits a little too much oscillation. More tweaks are needed to smooth out the climb. Obviously, the rougher the weather, the more pronounced the oscillation.

Detailed steps:

1. Backup your v1.3 flight_model.cfg in case this mod doesn't work for you / meet your expectations. You can restore it.

2. Download my modded flight_model.cfg file (Changed to Google Drive) -->

https://drive.google.com/file/d/1PF1He9oFjnifswOwECeaEVfaaPWyuETQ/view?usp=sharing

3. Replace the original with my modded flight_model.cfg. 

4. As mentioned in 1, if you don't like it, replace my modded flight_model.cfg file with the original backup you saved. Sorry I wasted your time. I know standards and expectations are very high.

Good luck. Hope it works for you.

Edited April 4, 20215 yr by tod

To the haters of BREDOK3D  who don't miss an opportunity to spew their hate, like flies on sheeet! How is the CRJ working out for you?  Can you take it down to 200 ft AGL in IMC weather  and then land it successfully using the ILS? You could with the 737 from Bredok3d just fine.

My two fav airliners are the 737 (v1.2. I admit v1.3 breaks more things than fixing things)) and the A330 (currently my fav since it satiates the  absence of the PMDG 777). I have parked the CRJ cause their ILS, GS sucks.  Aerosoft would fix it, they have the reputation and I trust them and I'll fly it when its all fixed up.

Edited April 4, 20215 yr by Manny

Opened a ticket yesterday. Received email and had a teamviewer session today with the dev. He's in Italy. He resolved my CTD issue, was a corrupt gauge file.. Took a three hour shakedown flight and was very pleased. I'd call that excellent support.

FWIW, on my flight I set up a FLC climb at 200kts to FL30 and it was a smooth climb at around 1500fpm IIRC.

May not be perfect but it's a fun a/c to fly around in. Definitely not study level but fun.

 

1 hour ago, tod said:

I don't normally post my mods since the FS community generally has very high expectations and preferences vary. But this scenario is an exception because the product's quality is inferior, and the updated aerodynamic settings in V1.3 is flawed and not thoroughly tested.

Having said that, I do like elements of the V1.3 updates like the sound, pitot heat and yaw damper so instead of going back to V1.2, I decided to mod. This performance mod specifically addresses the climbing issues above FL20.  It is NOT perfect, as the climb at that level still exhibits a little too much oscillation. More tweaks are needed to smooth out the climb. Obviously, the rougher the weather, the more pronounced the oscillation.

Detailed steps:

1. Backup your v1.3 flight_model.cfg in case this mod doesn't work for you / meet your expectations. You can restore it.

2. Download my modded flight_model.cfg file -->

https://mega.nz/file/FUcXVABB#Z2m7GUbtxqCme7IoHFF0t-6A4tOZX6j8sxxBDTS1Q7Q

3. Replace the original with my modded flight_model.cfg. 

4. As mentioned in 1, if you don't like it, replace my modded flight_model.cfg file with the original backup you saved. Sorry I wasted your time. I know standards and expectations are very high.

Good luck. Hope it works for you.

Unable to download, the file is greyed out and the site asks you to become a member. Can you post the text file (v1.3 flight_model.cfg )?

5 minutes ago, aero943 said:

Unable to download, the file is greyed out and the site asks you to become a member. Can you post the text file (v1.3 flight_model.cfg )?

Sorry this is the entire text content in the modded flight_model.cfg file.

 

[VERSION]
major = 1
minor = 0

[WEIGHT_AND_BALANCE]
max_gross_weight = 174200 ; Empty weight, (LBS)
empty_weight = 90710 ; Empty weight, (LBS)
reference_datum_position = 0, 0, 0 ; Position of reference datum relative to FS(0,0,0) (FEET), z, x, y
empty_weight_CG_position = -9, 0, -1 ; Position of airplane empty weight CG relative to reference datum (FEET), z, x, y
CG_forward_limit = 0.16 ; Gravity center forward limit (longitudinal offset) for longitudinal stability
CG_aft_limit = 0.4 ; Gravity center after limit (longitudinal offset z) w.r.t reference datum for longitudinal stability (FEET)
empty_weight_pitch_MOI = 1886301 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET)
empty_weight_roll_MOI = 672652 ; Empty roll moment of inertia, Jzz (SLUG SQ FEET)
empty_weight_yaw_MOI = 4193105 ; Empty yaw moment of inertia, Jyy (SLUG SQ FEET)
empty_weight_coupled_MOI = 1000 ; Empty transverse moment of inertia, Jyz (SLUG SQ FEET)
activate_mach_limit_based_on_cg = 0 ; Activate mach limitation depending on CG position (true if > 0 /false othewise). Mostly for Concorde).
activate_cg_limit_based_on_mach = 0 ; Activate cg limitation depending on mach value (true if > 0 /false othewise). Mostly for Concorde).
max_number_of_stations = 6 ; Number of payload stations
station_load.0 = 170, 35.59, -1.86, 5.017127, TT:MENU.PAYLOAD.PILOT, 1
station_load.1 = 170, 35.59, 1.86, 5.017127, TT:MENU.PAYLOAD.COPILOT, 2
station_load.2 = 6115, 22.845893, 0, 5.039792, TT:MENU.PAYLOAD.BUSINESS_CLASS, 0
station_load.3 = 3505, 26.825772, 0, 0.94849, TT:MENU.PAYLOAD.FORWARD_BAGGAGE, 0
station_load.4 = 4000, -21.223969, -4, 5.0, TT:MENU.PAYLOAD.ECONOMY_CLASS, 0
station_load.5 = 6310, -35.825745, 0.000001, 1.007935, TT:MENU.PAYLOAD.REAR_BAGGAGE, 0

[CONTACT_POINTS]
static_pitch = -0.2 ; degrees, pitch when at rest on the ground (+=Up, -=Dn)
static_cg_height = 8.89 ; feet, altitude of CG when at rest on the ground
gear_system_type = 1 ; gear system type (betweeen 0 and 4) 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none, 5 = undefined
tailwheel_lock = 0 ; Is tailwheel lock available TRUE/FALSE
max_number_of_points = 9 ; Number of contact points
gear_locked_on_ground = 0 ; Defines whether or not the landing gear handle is locked to down when the plane is on the ground.
gear_locked_above_speed = -1 ; Defines the speed at which the landing gear handle becomes locked in the up position. (-1 = Disabled)
max_speed_full_steering = 8 ; Defines the speed under which the full angle of steering is available (in feet/second).
max_speed_decreasing_steering = 50 ; Defines the speed above which the angle of steering stops decreasing (in feet/second).
min_available_steering_angle_pct = 0.2 ; Defines the percentage of steering which will always be available even above max_speed_decreasing_steering (in percent over 100).
max_speed_full_steering_castering = 20 ; Defines the speed under which the full angle of steering is available for free castering wheels (in feet/second).
max_speed_decreasing_steering_castering = 40 ; Defines the speed above which the angle of steering stops decreasing for free castering wheels  (in feet/second).
min_castering_angle = 0.05236 ; Defines the minimum angle a free castering wheel can take (in radians).
max_castering_angle = 3.14159265358979 ; Defines the maximum angle a free castering wheel can take (in radians).
point.0 = 1, 27.1, 0, -9.3, 720, 0, 1.68, 75, 0.555, 2, 0.33, 9, 9.4, 0, 0, 0, 2
point.1 = 1, -13, -14, -9.58, 1500, 1, 1.68, 0, 0.637, 2, 0.33, 9.7, 9, 2, 0, 0, 2
point.2 = 1, -13, 14, -9.58, 1500, 2, 1.68, 0, 0.637, 2, 0.33, 9.2, 9.9, 3, 0, 0, 2
point.3 = 2, -26, -57, 6, 100, 0, 0, 0, 0, 0, 0, 0, 0, 5, 0, 0, 1
point.4 = 2, -26, 57, 6, 100, 0, 0, 0, 0, 0, 0, 0, 0, 6, 0, 0, 1
point.5 = 2, -79.2, 0, 8, 100, 0, 0, 0, 0, 0, 0, 0, 0, 9, 0, 0, 1
point.6 = 2, 45, 0, 2, 720, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1
point.7 = 2, -68, 0, 4.1, 100, 0, 0, 0, 0, 0, 0, 0, 0, 7, 0, 0, 1
point.8 = 2, -75.2, 0, 32.3, 100, 0, 0, 0, 0, 0, 0, 0, 0, 8, 0, 0, 1

[FUEL]
LeftMain = -9, -13, 2, 1288, 0 ; For each tank: Tank position (z longitudinal, x lateral, y vertical) (FEET), total fuel capacity (GALLONS), unusable fuel capacity (GALLONS)
RightMain = -9, 13, 2, 1288, 0
Center1 = -11, 0, 1, 4299, 0
Center2 = 0, 0, 0, 0, 0
Center3 = 0, 0, 0, 0, 0
LeftAux = -13, -27, 3, 200, 0
LeftTip = 0, 0, 0, 0, 0
RightAux = -13, 27, 3, 200, 0
RightTip = 0, 0, 0, 0, 0
External1 = 0, 0, 0, 0, 0
External2 = 0, 0, 0, 0, 0
fuel_type = 2 ; 1 = OCTANE 100, 2 = JET_A, 3 = OCTANE 80, 4 = AUTO GAS, 5 = JET B
number_of_tank_selectors = 1 ; Max 4
electric_pump = 0
engine_driven_pump = 1
manual_transfer_pump = 0
manual_pump = 0
anemometer_pump = 0
fuel_dump_rate = 0.02
default_fuel_tank_selector.1 = 1 ; Default fuel selector used in case of autostart for engine 1, default is ALL.
default_fuel_tank_selector.2 = 1 ; Default fuel selector used in case of autostart for engine 2, default is ALL.
default_fuel_tank_selector.3 = 1 ; Default fuel selector used in case of autostart for engine 3, default is ALL.
default_fuel_tank_selector.4 = 1 ; Default fuel selector used in case of autostart for engine 4, default is ALL.

[FUEL_SYSTEM]
APU.1 = Name:APU#FuelBurnRate:33
Engine.1 = Name:LeftEngine#Index:1
Engine.2 = Name:RightEngine#Index:2
Tank.1 = Name:Center#Title:TT:MENU.FUEL.CENTER#Capacity:4299#UnusableCapacity:0#Position:-6,0,1#Priority:1#OutputOnlyLines:TankrToCenterTankCentePump1,TankCenterToCenterTankPump2
Tank.2 = Name:LeftInner#Title:TT:MENU.FUEL.LEFT_INNER#Capacity:1288#UnusableCapacity:0#Position:-8,-13,2#Priority:2#InputOnlyLines:Eng1ToTank2,Xfer1ToTank2,Xfer1ToTank2_2#OutputOnlyLines:TankLeftToLeftTankPump1,TankLeftToLeftTankPump2
Tank.3 = Name:RightInner#Title:TT:MENU.FUEL.RIGHT_INNER#Capacity:1288#UnusableCapacity:0#Position:-8,13,2#Priority:2#InputOnlyLines:Eng2ToTank3,Xfer2ToTank3,Xfer2ToTank3_2#OutputOnlyLines:TankRightToRightTankPump1,TankRightToRightTankPump2
Tank.4 = Name:LeftOuter#Title:TT:MENU.FUEL.LEFT_OUTER#Capacity:200#UnusableCapacity:0#Position:-13,-27,3#Priority:3#OutputOnlyLines:Tank4ToXfer1,Tank4ToXfer1_2
Tank.5 = Name:RightOuter#Title:TT:MENU.FUEL.RIGHT_OUTER#Capacity:200#UnusableCapacity:0#Position:-13,27,3#Priority:3#OutputOnlyLines:Tank5ToXfer2,Tank5ToXfer2_2
Line.1 = Name:TankCenterToCenterTankPump1#Source:Center#Destination:CenterTankPump1
Line.2 = Name:TankLeftToLeftTankPump1#Source:LeftInner#Destination:LeftInnerTankPump1
Line.3 = Name:TankRightToRightTankPump1#Source:RightInner#Destination:RightInnerTankPump1
Line.4 = Name:TankCenterToCenterTankPump2#Source:Center#Destination:CenterTankPump2
Line.5 = Name:TankLeftToLeftTankPump2#Source:LeftInner#Destination:LeftInnerTankPump2
Line.6 = Name:TankRightToRightTankPump2#Source:RightInner#Destination:RightInnerTankPump2
Line.7 = Name:PumpCenterToJuncLeftCenter#Source:CenterTankPump1#Destination:CenterLeftJunction
Line.8 = Name:PumpLeft1ToJuncLeft#Source:LeftInnerTankPump1#Destination:LeftJunction
Line.9 = Name:PumpRight1ToJuncRight#Source:RightInnerTankPump1#Destination:RightJunction
Line.10 = Name:PumpCenter2ToJuncRightCenter#Source:CenterTankPump2#Destination:CenterRightJunction
Line.11 = Name:PumpLeft2ToJuncLeft#Source:LeftInnerTankPump2#Destination:LeftJunction
Line.12 = Name:PumpRight2ToJuncRight#Source:RightInnerTankPump2#Destination:RightJunction
Line.13 = Name:Junc1ToEngValveLeft#Source:LeftJunction#Destination:LeftEngineValve
Line.14 = Name:Junc2ToEngValveRight#Source:RightJunction#Destination:RightEngineValve
Line.15 = Name:JuncAPUToAPUPump#Source:APUJunction#Destination:APUPump
Line.16 = Name:Junc1ToJuncAPU#Source:LeftJunction#Destination:APUJunction
Line.17 = Name:JuncAPUToJunc3#Source:APUJunction#Destination:CenterLeftJunction
Line.18 = Name:Junc3ToXFeed#Source:CenterLeftJunction#Destination:CrossFeedValve
Line.19 = Name:Junc4ToXFeed#Source:CenterRightJunction#Destination:CrossFeedValve
Line.20 = Name:Junc2ToJunc4#Source:RightJunction#Destination:CenterRightJunction
Line.21 = Name:Pump6ToAPUValve#Source:APUPump#Destination:APUValve
Line.22 = Name:APUValveToAPU#Source:APUValve#Destination:APU
Line.23 = Name:Eng1ToTank2#Source:LeftEngine#Destination:LeftInner
Line.24 = Name:Eng2ToTank3#Source:RightEngine#Destination:RightInner
Line.25 = Name:EngValveLeftToEngLeft#Source:LeftEngineValve#Destination:LeftEngine
Line.26 = Name:EngValveRightToEngRight#Source:RightEngineValve#Destination:RightEngine
Line.27 = Name:Tank4ToXfer1#Source:LeftOuter#Destination:LeftTransferValve1#GravityBasedFuelFlow:500
Line.28 = Name:Tank5ToXfer2#Source:RightOuter#Destination:RightTransferValve1#GravityBasedFuelFlow:500
Line.29 = Name:Xfer1ToTank2#Source:LeftTransferValve1#Destination:LeftInner#GravityBasedFuelFlow:500
Line.30 = Name:Xfer2ToTank3#Source:RightTransferValve1#Destination:RightInner#GravityBasedFuelFlow:500
Line.31 = Name:Tank4ToXfer1_2#Source:LeftOuter#Destination:LeftTransferValve2#GravityBasedFuelFlow:500
Line.32 = Name:Tank5ToXfer2_2#Source:RightOuter#Destination:RightTransferValve2#GravityBasedFuelFlow:500
Line.33 = Name:Xfer1ToTank2_2#Source:LeftTransferValve2#Destination:LeftInner#GravityBasedFuelFlow:500
Line.34 = Name:Xfer2ToTank3_2#Source:RightTransferValve2#Destination:RightInner#GravityBasedFuelFlow:500
Junction.1 = Name:LeftJunction#InputOnlyLines:PumpLeft1ToJuncLeft,PumpLeft2ToJuncLeft#OutputOnlyLines:Junc1ToEngValveLeft,Junc1ToJuncAPU
Junction.2 = Name:RightJunction#InputOnlyLines:PumpRight1ToJuncRight#OutputOnlyLines:Junc2ToEngValveRight
Junction.3 = Name:CenterLeftJunction#InputOnlyLines:PumpCenterToJuncLeftCenter
Junction.4 = Name:CenterRightJunction#InputOnlyLines:PumpCenter2ToJuncRightCenter
Junction.5 = Name:APUJunction#OutputOnlyLines:JuncAPUToAPUPump
Valve.1 = Name:LeftEngineValve#OpeningTime:3#Circuit:1
Valve.2 = Name:RightEngineValve#OpeningTime:3#Circuit:2
Valve.3 = Name:CrossFeedValve#OpeningTime:3#Circuit:3
Valve.4 = Name:LeftTransferValve2#Circuit:4
Valve.5 = Name:RightTransferValve2#Circuit:5
Valve.6 = Name:LeftTransferValve1#Circuit:6
Valve.7 = Name:RightTransferValve1#Circuit:7
Valve.8 = Name:APUValve#OpeningTime:3#Circuit:8
Pump.1 = Name:CenterTankPump1#Pressure:29#DestinationLine:PumpCenterToJuncLeftCenter#TankFuelRequired:Center#Type:Electric#Index:1
Pump.2 = Name:LeftInnerTankPump1#Pressure:25#DestinationLine:PumpLeft1ToJuncLeft#TankFuelRequired:LeftInner#Type:Electric#Index:3
Pump.3 = Name:RightInnerTankPump1#Pressure:25#DestinationLine:PumpRight1ToJuncRight#TankFuelRequired:RightInner#Type:Electric#Index:4
Pump.4 = Name:CenterTankPump2#Pressure:29#DestinationLine:PumpCenter2ToJuncRightCenter#TankFuelRequired:Center#Type:Electric#Index:2
Pump.5 = Name:LeftInnerTankPump2#Pressure:25#DestinationLine:PumpLeft2ToJuncLeft#TankFuelRequired:LeftInner#Type:Electric#Index:5
Pump.6 = Name:RightInnerTankPump2#Pressure:25#DestinationLine:PumpRight2ToJuncRight#TankFuelRequired:RightInner#Type:Electric#Index:6
Pump.7 = Name:APUPump#Pressure:5#DestinationLine:Pump6ToAPUValve#TankFuelRequired:LeftInner#Type:APUDriven
Trigger.1 = Target:LeftInner#Threshold:250#Condition:TankQuantityBelow#EffectTrue:OpenValve.LeftTransferValve1,OpenValve.LeftTransferValve2#EffectFalse:CloseValve.LeftTransferValve1,CloseValve.LeftTransferValve2
Trigger.2 = Target:RightInner#Threshold:250#Condition:TankQuantityBelow#EffectTrue:OpenValve.RightTransferValve1,OpenValve.RightTransferValve2#EffectFalse:CloseValve.RightTransferValve1,CloseValve.RightTransferValve2
Trigger.3 = Condition:Autostart_Enabled#EffectTrue:OpenValve.LeftEngineValve,OpenValve.RightEngineValve,OpenValve.CrossFeedValve,OpenValve.APUValve,StartPump.CenterTankPump1,StartPump.LeftInnerTankPump1,StartPump.RightInnerTankPump1,StartPump.CenterTankPump2,StartPump.LeftInnerTankPump2,StartPump.RightInnerTankPump2,StartPump.APUPump
Trigger.4 = Condition:Autoshutdown_Enabled#EffectTrue:CloseValve.LeftEngineValve,CloseValve.RightEngineValve,CloseValve.CrossFeedValve,CloseValve.APUValve,StopPump.CenterTankPump1,StopPump.LeftInnerTankPump1,StopPump.RightInnerTankPump1,StopPump.CenterTankPump2,StopPump.LeftInnerTankPump2,StopPump.RightInnerTankPump2

[AIRPLANE_GEOMETRY]
wing_area = 1313.2 ; Wing area S (SQUARE FEET)
wing_span = 117.454 ; Wing span b (FEET)
wing_root_chord = 25.8 ; Wing root chord croot (FEET)
wing_camber = 1 ; (DEGREES)
wing_thickness_ratio = 0.02 ; Local thickness is local_chord(x)*wing_thickness_ratio, x = lateral coord
wing_dihedral = 6.0 ; Dihedral angle Lambda (DEGREES)
wing_incidence = 2 ; Wing incidence (DEGREES)
wing_twist = -0.5 ; Wing twist epsilon (DEGREES)
oswald_efficiency_factor = 0.68 ; Wing Oswald efficiency factor e (non dimensional)
wing_winglets_flag = 0 ; Has winglets true/false
wing_sweep = 25 ; Wing sweep (DEGREES)
wing_pos_apex_lon = 0 ; Longitudinal (z) position of wing apex w.r.t reference datum (FEET)
wing_pos_apex_vert = 0 ; Vertical (y) position of wing apex w.r.t reference datum (FEET)
htail_area = 352 ; Horizontal tail area (SQUARE FEET)
htail_span = 41.3 ; Horizontal tail span (FEET)
htail_pos_lon = -70 ; Longitudinal (z) position of horizontal tail  w.r.t reference datum (FEET)
htail_pos_vert = 9 ; Vertical (y) position of horizontal tail  w.r.t reference datum (FEET)
htail_incidence = 0 ; Horizontal tail incidence (DEGREES)
htail_sweep = 30 ; Horizontal tail sweep angle (DEGREES)
htail_thickness_ratio = 0.02 ; Local thickness is local_chord(x)*htail_thickness_ratio, x = lateral coord
vtail_area = 284.5 ; Vertical tail area (SQUARE FEET)
vtail_span = 23.5 ; Vertical tail span (FEET)
vtail_sweep = 35 ; Vertical tail sweep angle (DEGREES)
vtail_pos_lon = -65 ; Longitudinal (z) position of vertical tail  w.r.t reference datum (FEET)
vtail_pos_vert = 19.5 ; Vertical (y) position of vertical tail  w.r.t reference datum (FEET)
vtail_thickness_ratio = 0.03 ; Local thickness is local_chord(x)*vtail_thickness_ratio, x = lateral coord
fuselage_length = 129 ; Nose to tail (FEET)
fuselage_diameter = 13
fuselage_center_pos = -5, 0, 5
elevator_area = 10 ; Elevator area (SQUARE FEET 200 orig)
aileron_area = 6 ; Elevator area (SQUARE FEET)
rudder_area = 20 ; Elevator area (SQUARE FEET)
elevator_up_limit = 8 ; Elevator max deflection up angle (DEGREES)
elevator_down_limit = 8 ; Elevator max deflection down angle (absolute value) (DEGREES)
aileron_up_limit = 10 ; Aileron max deflection  angle (DEGREES)
aileron_down_limit = 10 ; Aileron max deflection down angle (absolute value) (DEGREES)
rudder_limit = 25 ; Rudder max deflection angle (absolute value) (DEGREES)
rudder_trim_limit = 20 ; Rudder trim max deflection angle (absolute value) (DEGREES)
elevator_trim_limit = 12.5 ; Elevator trim max angle (absolute value) (DEGREES)
spoiler_limit = 23 ; Spoiler max deflection angle (absolute value) (DEGREES)
spoilerons_available = 1 ; Aircraft has spoilerons true/false
aileron_to_spoileron_gain = 1.0 ; Aileron influence on spoileron angle (non-dimensional)
min_ailerons_for_spoilerons = 2 ; Minimum aileron deflection (absolute value) in which spoilerons are active (DEGREES)
min_flaps_for_spoilerons = 0 ; Minimum flaps deflection (absolute value) in which spoilerons are active (DEGREES)
spoiler_extension_time = 2 ; Spoilers extension time (SECONDS)
spoiler_handle_available = 1 ; Spoiler handles available true/false
auto_spoiler_available = 1 ; Auto spoilers available true/false
auto_spoiler_auto_retracts = 0 ; Auto spoilers retracts automatically true/false
auto_spoiler_min_speed = 72 ; Auto spoilers minimum trigger speed
positive_g_limit_flaps_up = 2.5 ; Flap positive load limit when up. Same dimension as gravity vector FEET/SECONDS^2
positive_g_limit_flaps_down = 2.0 ; Flap positive load limit when down. Same dimension as gravity vector FEET/SECONDS^2
negative_g_limit_flaps_up = -0.5 ; Flap negative load limit when up. Same dimension as gravity vector FEET/SECONDS^2
negative_g_limit_flaps_down = 0.0 ; Flap negative load limit when down. Same dimension as gravity vector FEET/SECONDS^2
load_safety_factor = 1.5 ; Flap negative load limit when down. Same dimension as gravity vector FEET/SECONDS^2
elevator_trim_neutral = 0 ; Elevator trim max angle (absolute value) (DEGREES), for indicators only (no influence on flight model)
aileron_to_rudder_scale = 0 ; non-dimensional
flap_to_aileron_scale = 0 ; non-dimensional
fly_by_wire = 0 ; Fly-by-wire available true/false
elevator_elasticity_table = 0:1, 90:0.8, 250:0.6, 400:0.33
aileron_elasticity_table = 0:1, 90:0.8, 250:0.6, 400:0.33
rudder_elasticity_table = 0:1, 90:0.8, 250:0.6, 400:0.33
elevator_trim_elasticity_table = 0:0.8, 120:0.7, 250:0.6, 400:0.33

[AERODYNAMICS]
lift_coef_pitch_rate = -59.406 ; The change in lift per change in pitch rate
lift_coef_daoa = 0 ; lift per change in angle of attack rate
lift_coef_delta_elevator = -0.374 ; The change in lift per change in elevator deflection
lift_coef_horizontal_incidence = 0 ; The change in lift per change in horizontal incidence angle
lift_coef_flaps = 1.0459 ; Change in lift due to flaps
lift_coef_spoilers = -0.30000 ; Change in lift due to spoilers
drag_coef_zero_lift = 0.0250 ; The zero lift drag polar
drag_coef_flaps = 0.1595
drag_coef_gear = 0.005
drag_coef_spoilers = 0.15000
side_force_slip_angle = -1.315 ; (yaw angle) The change in side force per change in side slip angle
side_force_roll_rate = 1.54 ; (roll velocity)  The change in side force per change in roll rate
side_force_yaw_rate = 12.138 ; (yaw velocity) The change in side force per change in yaw rate
side_force_delta_rudder = -0.555 ; 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 = -1.273 ; The change in pitch moment per change in elevator deflection
pitch_moment_delta_trim = -1.273 ; The change in pitch moment per change in trim
pitch_moment_pitch_damping = -3661 ; The change in pitch moment per change in pitch rate(PRIMARY PITCH STABILITY FACTOR). deg/s
pitch_moment_aoa_0 = -0.16 ; Pitch moment at zero angle - of - attack
pitch_moment_daoa = 0 ; The change in pitch moment per change in angle of attack
pitch_moment_flaps = -0.135 ; The pitch moment due to flaps
pitch_moment_gear = 0.002 ; The pitch moment due to gear
pitch_moment_spoilers = -0.09285 ; The pitch moment due to spoilers
pitch_moment_delta_elevator_propwash = 0
pitch_moment_pitch_propwash = 0
roll_moment_slip_angle = 0.25 ; The change in roll moment per sideslip angle(DIHEDRAL EFFECT)
roll_moment_roll_damping = -8.354
roll_moment_yaw_rate = -1.421
roll_moment_spoilers = 0 ; The change in roll moment due to spoilers
roll_moment_delta_aileron = -0.116 ; (control)The change in roll moment per change in aileron deflection
roll_moment_delta_rudder = -0.075 ; (control)The change in roll moment per change rudder deflection
roll_moment_delta_aileron_trim_scalar = -0.119 ; Change in roll moment due to aileron trim
yaw_moment_slip_angle = 0.104 ; The change in yaw moment per change sideslip angle(WEATHER VANING EFFECT)
yaw_moment_roll = 0.378 ; (adverse yaw) The change in yaw moment per change in roll rate deg/s
yaw_moment_yaw_damping = -99.265 ; (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 = -0.004 ; (adverse yaw)  The change in yaw moment per change aileron deflection
yaw_moment_delta_rudder = 0.278 ; (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 = 0.278 ; Change in yaw moment due to rudder trim
compute_aero_center = 0
aero_center_lift = -7.0 ; Init to center
lift_coef_aoa_table = -3.15:0, -0.8:-1.154, -0.4:-0.928, -0.2:-0.781, -0.1:-0.372, 0:0.250, 0.20:1.215, 0.23:1.293, 0.26:1.314, 0.29:1.117, 0.31:1.049, 0.4:0.941, 0.8:1.183, 3.15:0
lift_coef_ground_effect_mach_table = 0.054:1.25
lift_coef_mach_table = 0:1
lift_coef_delta_elevator_mach_table = 0:0
lift_coef_daoa_mach_table = 0:0
lift_coef_pitch_rate_mach_table = 0:0
lift_coef_horizontal_incidence_mach_table = 0:0
drag_coef_zero_lift_mach_tab = 0:0.000, 0.5:0.000, 0.55:0.000, 0.6:0.000, 0.65:0.000, 0.7:0.000, 0.75:0.000, 0.8:0.000, 0.85:0.000, 0.9:0.000, 0.95:0.100, 1.0:1.000, 1.1:0.532, 1.5:0.046
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:-0.004885, 1:-0.004885, 1.2:-0.004885, 1.4:-0.004885, 1.6:-0.004885, 1.8:-0.004885, 2:-0.004885, 2.2:-0.004885, 2.4:-0.004885, 2.6:-0.004885, 2.8:-0.004885, 3:-0.004885, 3.2:-0.004885
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 = -3.14159:-2, -0.43633:-0.62641, -0.2618:-0.43412, 0:0, 0.17453:0.4658, 0.2618:0.14272, 0.31416:0.20041, 0.34907:0.1, 0.43633:0.15, 3.14159:2
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, 0.2:0.067904, 0.4:0.135809, 0.6:0.203713, 0.8:0.303859, 1:0.404006, 1.2:0.404006, 1.4:0.404006, 1.6:0.404006, 1.8:0.404006, 2:0.404006, 2.2:0.404006, 2.4:0.404006, 2.6:0.404006, 2.8:0.404006, 3:0.404006, 3.2:0.404006
pitch_moment_daoa_mach_table = 0:0, 0.2:0.024915, 0.4:0.100147, 0.6:0.275037, 0.8:0.750366, 1:1.000489, 1.2:0, 1.4:-3.001466, 1.6:-4.001954, 1.8:-4.502198, 2:-5.002443, 2.2:-5.002443, 2.4:-5.002443, 2.6:-5.002443, 2.8:-5.002443, 3:-5.002443, 3.2:-5.002443
pitch_moment_pitch_rate_mach_table = 0:0, 0.2:0, 0.4:-0.062531, 0.6:-0.125061, 0.8:-0.187592, 1:-0.250122, 1.2:-0.187592, 1.4:-0.125061, 1.6:-0.062531, 1.8:0, 2:0.125061, 2.2:0.250122, 2.4:0.250122, 2.6:0.250122, 2.8:0.250122, 3:0.250122, 3.2:0.250122
pitch_moment_horizontal_incidence_mach_table = 0:0, 0.2:0.049829, 0.4:0.100147, 0.6:0.200293, 0.8:0.500244, 1:0.350269, 1.2:0.350269, 1.4:0.350269, 1.6:0.350269, 1.8:0.350269, 2:0.350269, 2.2:0.350269, 2.4:0.350269, 2.6:0.350269, 2.8:0.350269, 3:0.350269, 3.2:0.350269
pitch_moment_aoa_0_mach_table = 0:0, 0.2:0, 0.4:0, 0.6:0, 0.8:0.000489, 1:0.019541, 1.2:0.00977, 1.4:0.00977, 1.6:0.00977, 1.8:0.00977, 2:0.00977, 2.2:0.00977, 2.4:0.00977, 2.6:0.00977, 2.8:0.00977, 3:0.00977, 3.2:0.00977
roll_moment_aoa_table = -17:0, -10:0, -6:0, 10:0, 12:0, 13:0, 17:0 ; Cl (roll moment coef) versus AoA
roll_moment_slip_angle_aoa_table = -180:1, -90:0.2, -18:0.2, -10:0.8, 0:1, 10:0.8, 18:0.2, 90:0.2, 180:1
roll_moment_roll_rate_aoa_table = -180:1, -90:0.3, -18:0.4, -10:0.6, 0:1, 10:0.6, 18:0.4, 90:0.3, 180:1
roll_moment_delta_aileron_aoa_table = -15:1, 0:1, 13:1, 16:1, 25:1
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:-0.004885, 0.6:-0.010259, 0.8:-0.020029, 1:-0.024915, 1.2:-0.024915, 1.4:-0.024915, 1.6:-0.024915, 1.8:-0.024915, 2:-0.024915, 2.2:-0.024915, 2.4:-0.024915, 2.6:-0.024915, 2.8:-0.024915, 3:-0.024915, 3.2:-0.024915
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:-0.004885, 0.4:-0.020029, 0.6:-0.049829, 0.8:-0.100147, 1:-0.109917, 1.2:-0.109917, 1.4:-0.109917, 1.6:-0.109917, 1.8:-0.109917, 2:-0.109917, 2.2:-0.109917, 2.4:-0.109917, 2.6:-0.109917, 2.8:-0.109917, 3:-0.109917, 3.2:-0.109917
yaw_moment_aoa_table = -16:0, -13:0, -10:0, 10:0, 11:0, 13:0, 15:0 ; Cn (yaw moment coef) versus AoA
yaw_moment_slip_angle_aoa_table = -180:1, -90:0, -18:0.2, -10:0.3, 0:1, 10:0.3, 18:0.2, 90:0, 180:1
yaw_moment_yaw_rate_aoa_table = -180:1, -90:0.1, -18:0.2, -10:0.4, 0:1, 10:0.4, 18:0.2, 90:0.1, 180:1
yaw_moment_delta_rudder_aoa_table = -15:1, 0:1, 13:1, 16:1, 25:1
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:-0.000977, 0.6:-0.001954, 0.8:-0.002931, 1:-0.002931, 1.2:-0.002931, 1.4:-0.002931, 1.6:-0.002931, 1.8:-0.002931, 2:-0.002931, 2.2:-0.002931, 2.4:-0.002931, 2.6:-0.002931, 2.8:-0.002931, 3:-0.002931, 3.2:-0.002931
yaw_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
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 = -0.785:0.5, -0.524:0.85, -0.175:0.9, 0:1, 0.175:0.9, 0.524:0.85, 0.785:0.5 ; scales control based on its deflection
aileron_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
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 ; scales control based on its deflection
aileron_load_factor_effectiveness_table = 0:1 ; scaling of roll_moment_delta_aileron versus gravity forces, G effects on aileron effectiveness, acts on roll_moment_delta_aileron
lift_coef_at_drag_zero = 0.3
lift_coef_at_drag_zero_flaps = 0.3

[FLIGHT_TUNING]
cruise_lift_scalar = 1.61
parasite_drag_scalar = 0.4
induced_drag_scalar = 0.982
flap_induced_drag_scalar = 1
elevator_effectiveness = 1
elevator_maxangle_scalar = 0.8
aileron_effectiveness = 0.8
rudder_effectiveness = 1
rudder_maxangle_scalar = 0.5
pitch_stability = 0.25
roll_stability = 0.25
yaw_stability = 0.25
pitch_gyro_stability = 1
roll_gyro_stability = 1
yaw_gyro_stability = 1
elevator_trim_effectiveness = 1
aileron_trim_effectiveness = 1
rudder_trim_effectiveness = 1
hi_alpha_on_roll = 0
hi_alpha_on_yaw = 0
p_factor_on_yaw = 0
torque_on_roll = 0
gyro_precession_on_roll = 0
gyro_precession_on_yaw = 0
engine_wash_on_roll = 0 ; Torque effect
wingflex_scalar = 0.75
wingflex_offset = -0.25
stall_coef_at_min_weight = 0.71

[REFERENCE SPEEDS]
full_flaps_stall_speed = 121 ; Knots True (KTAS)
flaps_up_stall_speed = 179 ; Knots True (KTAS)
cruise_speed = 455 ; Knots True (KTAS)
cruise_mach = 0.78
crossover_speed = 320 ; Knots Indicated (KIAS)
max_mach = 0.82
max_indicated_speed = 500 ; Red line (KIAS)
max_flaps_extended = 274.030126
normal_operating_speed = 360
airspeed_indicator_max = 562.5
rotation_speed_min = 135 ; Min speed required (Kts)
climb_speed = 231 ; Climb speed (Kts)
cruise_alt = 36000 ; (ft)
takeoff_speed = 150 ; Takeoff Speed (Kts)
spawn_cruise_altitude = 5000 ; Spawn Cruise Altitude (ft)
spawn_descent_altitude = 500 ; Spawn Descent Altitude (ft)
best_angle_climb_speed = 0 ; Best angle climb speed (Kts)
approach_speed = 0 ; Approach speed (Kts)
best_glide = 0 ; Best Glide (Kts)
max_gear_extended = 280 ; (Kts)

[INTERACTIVE POINTS]
number_of_interactive_points = 10
interactive_point.0 = 0.4, 32.65, -5.90, 1.70, 0, 0, 0, -86, 72, 16, 85, 3, -2, 33
interactive_point.1 = 0.4, -51.565, -5.2, 2.13, 0, 0, 0, -103, 0, 0, 0, 0, 0, 0
interactive_point.2 = 0.4, -51.565, -5.21, 2.13, 0, 0, 0, -103, 0, 0, 0, 0, 0, 0
interactive_point.3 = 0.4, -51.565, -5.2, 2.03, 0, 0, 0, -103, 0, 0, 0, 0, 0, 0
interactive_point.4 = 0.4, -39.327, 2.28, -1.738, 1, 0, 0, 90, 0, 0, 0, 0, 0, 0
interactive_point.5 = 0.4, 22.20, 2.46, -2.23, 1, 0, 0, 90, 0, 0, 0, 0, 0, 0
interactive_point.6 = 0.4, -4, -6, 6.2, 2, 0, 0, -90, 0, 0, 0, 0, 0, 0
interactive_point.7 = 0.4, -4, 6, 6.2, 2, 0, 0, 90, 0, 0, 0, 0, 0, 0
interactive_point.8 = 0, 43.30, 7.26, -5.18, 4, 0, 0, 45, 0, 0, 0, 0, 0, 0
interactive_point.9 = 0, 0, -55.59, -7.57, 3, 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 = 2 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge
system_type = 1 ; Flap system type 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none
system_type_index = 80
span-outboard = 0.8 ; Outboard span area (added area) (percentage, non dimensional)
extending-time = 12 ; Flap extension time (SECONDS)
damaging-speed = 233 ; Speed above which flap is damaged (Kts)
blowout-speed = 250 ; Speed above which flap is blown out (Kts)
maneuvering_flaps = 0
lift_scalar = 0.2 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
drag_scalar = 0.2 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned)
pitch_scalar = 1 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned)
max_on_ground_position = 9 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found.
flaps-position.0 = 0, -1, 0
flaps-position.1 = 1, 250, 0.1
flaps-position.2 = 2, 230, 0.2
flaps-position.3 = 5, 220, 0.3
flaps-position.4 = 10, 200, 0.4
flaps-position-autoretract.1 = 0, 180, 230
flaps-position-inhibit.1 = air,increasing
flaps-position.5 = 15, 190, 0.5
flaps-position.6 = 25, 175, 0.6
flaps-position.7 = 30, 165, 0.75
flaps-position.8 = 40, 155, 1

[FLAPS.1]
type = 1 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge
system_type = 1 ; Flap system type 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none
system_type_index = 79
span-outboard = 0.75 ; Outboard span area (added area) (percentage, non dimensional)
extending-time = 12 ; Flap extension time (SECONDS)
damaging-speed = 260 ; Speed above which flap is damaged (Kts)
blowout-speed = 270 ; Speed above which flap is blown out (Kts)
maneuvering_flaps = 0
lift_scalar = 1.4 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
drag_scalar = 0.5 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned)
pitch_scalar = 1 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned)
max_on_ground_position = 9 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found.
flaps-position.0 = 0, -1, 0
flaps-position.1 = 1, 250, 0.1
flaps-position.2 = 2, 230, 0.2
flaps-position.3 = 5, 220, 0.3
flaps-position.4 = 10, 200, 0.4
flaps-position.5 = 15, 190, 0.5
flaps-position.6 = 25, 175, 0.6
flaps-position.7 = 30, 165, 0.75
flaps-position.8 = 40, 155, 1

40 minutes ago, Manny said:

Can you take it down to 200 ft AGL in IMC weather  and then land it successfully using the ILS?

I’m not hating on either and have never tried the 737, but yes, you definitely can do this lol

12 minutes ago, tod said:

 

Thank you.

1 hour ago, Manny said:

You could with the 737 from Bredok3d just fine.

Only if you can survive how the cockpit looks 😁

13 minutes ago, bendead said:

Only if you can survive how the cockpit looks 😁

The Cockpit is just fine.

 

What is it you dislike about this? Can you point out the differences? 

Edited April 5, 20215 yr by Manny

16 minutes ago, Manny said:

Can you point out the differences? 

From those pictures, maybe it's not what is different, but more like, what looks like the same.

Aerosoft CRJ is far from great right now, some stuff are really broken, but at least the external and cockpit model are awesome, even better than Asobo.

1 hour ago, Manny said:

The Cockpit is just fine.

 

What is it you dislike about this? Can you point out the differences? 

 

Literally everything lol

 

@TOD

I did a quick test flight KSAN-KPHX, the ascending rate with VNAV on was very good but during the climbing and leveling off the plane was oscillating like the early days of the B747-8i. I need to do more testing but getting at FL340 with VNAV on is a good start.

11 minutes ago, aero943 said:

@TOD

I did a quick test flight KSAN-KPHX, the ascending rate with VNAV on was very good but during the climbing and leveling off the plane was oscillating like the early days of the B747-8i. I need to do more testing but getting at FL340 with VNAV on is a good start.

I agree fully. The vertical oscillation is pretty annoying. More tweaking to come. Very much appreciate the feedback from your test flight aero943!

13 minutes ago, tod said:

I agree fully. The vertical oscillation is pretty annoying. More tweaking to come. Very much appreciate the feedback from your test flight aero943!

The oscillation was left to right. Thank you for your effort.

17 minutes ago, aero943 said:

The oscillation was left to right. Thank you for your effort.

Interesting I saw the ups and downs... Didn't see left to right oscillations. Thanks for the note, though. Hopefully I can address it in my next revision. .. Or better yet have the developer release a hot fix ASAP so that we can go back to flying.

Edited April 5, 20215 yr by tod