4 hours ago, Manny said:

The Cockpit is just fine.

 

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

I like the 737,

Things I see.

The airbus knobs, instead of the Boeing knobs in front of pilot.  they could fix that pretty easy.  The size of the autobrakes knob, its like they scaled it down a bit too much, its a little small.

Buts its really close other than little things,  I think its great for the price. 

The CRJ is super pretty,  love the calls from the back about to take off, serving sandwiches, the safety briefing,  announcing all the passengers are off or aboard.   

I don’t like it can’t do an ILS worth a word not allowed, even worse with new update.

I don’t like that it can’t use the built in nav, and can’t use ATC without programming a fake flight plan, then doing all the work to get the real flight plan inside the CRJ, to mimic the one from MS that does nothing.

I don’t know why people attacked the 737 as hard as they did, I have a speculation; it was folks that are developing one, and were really slow on the take.  Caught with their pants down...

 

 

 

On 4/4/2021 at 10:01 PM, aero943 said:

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

Hi Aero943,

Here is the latest flight dynamics for VNAV. I did 2 test flights KPDX - KLAS, and KSAN - KPHX. Fuel default 50%, Scattered Clouds, Day flight. 

Improvements to Climb oscillation and FL stability. I no longer see significant climb vertical oscillation (greatly reduced), and FL oscillation is barely noticeable. I still do not see horizontal oscillation but hopefully that is improved as well. While tweaking, I got a little OCD, thinking why does the takeoff lift feel so heavy? Maybe its just me, but getting this plane off the ground is a lot of effort >175kts and pulling the yoke all the way back. This is the 737MAX, so after some online research on performance, I've tweaked the takeoff to be around 145kts with more natural effort on the yoke (again at default 50% fuel weight). I think if behaves more realistic and to my personal liking. Your preference may vary.

The latest flight dynamics are here --> https://drive.google.com/file/d/1PF1He9oFjnifswOwECeaEVfaaPWyuETQ/view?usp=sharing

Text version. 

 [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 = 26 ; Elevator area (SQUARE FEET 200 orig)
aileron_area = 45 ; Elevator area (SQUARE FEET)
rudder_area = 20 ; Elevator area (SQUARE FEET)
elevator_up_limit = 18 ; Elevator max deflection up angle (DEGREES)
elevator_down_limit = 12 ; Elevator max deflection down angle (absolute value) (DEGREES)
aileron_up_limit = 19 ; Aileron max deflection  angle (DEGREES)
aileron_down_limit = 17 ; 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 = 13.5 ; 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, 90:1, 250:0.9, 400:0.33
aileron_elasticity_table = 0:1, 90:1, 250:0.9, 400:0.33
rudder_elasticity_table = 0:1, 90:1, 250:0.9, 400:0.33
elevator_trim_elasticity_table = 0:1, 120:1, 250:0.9, 400:0.33

[AERODYNAMICS]
lift_coef_pitch_rate = -56.44798
lift_coef_daoa = 0.0
lift_coef_delta_elevator = -1.36067
lift_coef_horizontal_incidence = 0.0
lift_coef_flaps = 1.045380
lift_coef_spoilers = 0.30000
drag_coef_zero_lift = 0.02370
drag_coef_flaps = 0.15660
drag_coef_gear = 0.00500
drag_coef_spoilers = 0.08500
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 = -6.0 ; Init to center
lift_coef_aoa_table = -3.15:0, -0.8:-1.231, -0.4:-0.917, -0.2:-0.772, -0.1:-0.246, 0:0.300, 0.20:1.118, 0.23:1.183, 0.26:1.231, 0.29:1.224, 0.31:1.071, 0.4:0.917, 0.8:1.240, 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, 0.9:0.150, 0.95:0.333, 1.0:0.500, 1.1:0.265, 1.5:0.030
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 = 0.3000
lift_coef_at_drag_zero_flaps = 0.3000

[FLIGHT_TUNING]
cruise_lift_scalar = 1.4
parasite_drag_scalar = 0.4
induced_drag_scalar = 0.982
flap_induced_drag_scalar = 1
elevator_effectiveness = 1.3
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

Good luck. Hope you like it. I'm more satisfied now compared with the developer's version, and can finally go back to enjoying the MAX.

On 4/5/2021 at 5:50 AM, karlz said:

I don’t know why people attacked the 737 as hard as they did, I have a speculation; it was folks that are developing one, and were really slow on the take.  Caught with their pants down...

That may be true, but of course any competitor is merely a spur to do better yourself, and so people who make good stuff are never really afraid of competition. Having said that, I'm aware this sort of thing goes on, for example, I know for sure that some youtube reviewers who've made videos on the same topics as ones I've covered, have voted down my videos; one even came at me with baseless accusations of some really nasty stuff, so I know it is true that some people don't really get the concept of friendly rivalry. I just think it's amusing when people try that sort of thing when they'd be better off concentrating on their own work; so most of the time it backfires on them spectacularly.

5 hours ago, tod said:

Hi Aero943,

Here is the latest flight dynamics for VNAV. I did 2 test flights KPDX - KLAS, and KSAN - KPHX. Fuel default 50%, Scattered Clouds, Day flight. 

Improvements to Climb oscillation and FL stability. I no longer see significant climb vertical oscillation (greatly reduced), and FL oscillation is barely noticeable. I still do not see horizontal oscillation but hopefully that is improved as well. While tweaking, I got a little OCD, thinking why does the takeoff lift feel so heavy? Maybe its just me, but getting this plane off the ground is a lot of effort >175kts and pulling the yoke all the way back. This is the 737MAX, so after some online research on performance, I've tweaked the takeoff to be around 145kts with more natural effort on the yoke (again at default 50% fuel weight). I think if behaves more realistic and to my personal liking. Your preference may vary.

Good luck. Hope you like it. I'm more satisfied now compared with the developer's version, and can finally go back to enjoying the MAX.

Congrats, you did a hell of a job. Great smooth take off, also smooth ascending /descending via VNAV. Two thumbs up, the developer should pay you for your mode. It brought the MAX back to my Community folder. It's very late here time to go to sleep. THANK YOU

I will try that later the day !

Thanks for your hard work on this.

Would make the plane come back to the hangar..

Report back after a testflight.

cheers 😉

3 hours ago, Chock said:

That may be true, but of course any competitor is merely a spur to do better yourself, and so people who make good stuff are never really afraid of competition. Having said that, I'm aware this sort of thing goes on, for example, I know for sure that some youtube reviewers who've made videos on the same topics as ones I've covered, have voted down my videos; one even came at me with baseless accusations of some really nasty stuff, so I know it is true that some people don't really get the concept of friendly rivalry. I just think it's amusing when people try that sort of thing when they'd be better off concentrating on their own work; so most of the time it backfires on them spectacularly.

Agree..I think it's about time the forums (fora) need to make it mandatory for their members to post verified signatures and age!

31 minutes ago, Peter Webber said:

Agree..I think it's about time the forums (fora) need to make it mandatory for their members to post verified signatures and age!

AND users should have to upload a 15 minute video explaining why the Bredok 737 is the best flight simulation product ever made before they’re allowed to post. We need to cleanse this forum (fora) of any voice that dare speaks against the Truth Of Bredok.

19 minutes ago, Chapstick said:

AND users should have to upload a 15 minute video explaining why the Bredok 737 is the best flight simulation product ever made before they’re allowed to post. We need to cleanse this forum (fora) of any voice that dare speaks against the Truth Of Bredok.

Shure nobody says Bredok 737 is the best product for MSFS - what a nonsens..

 

cheers

21 minutes ago, pmplayer said:

Shure nobody says Bredok 737 is the best product for MSFS - what a nonsens..

 

cheers

It's currently better than any other 737 out there for MSFS, and thats a fact  <innocent smile>

Graham

3 hours ago, aero943 said:

Congrats, you did a hell of a job. Great smooth take off, also smooth ascending /descending via VNAV. Two thumbs up, the developer should pay you for your mode. It brought the MAX back to my Community folder. It's very late here time to go to sleep. THANK YOU

At the moment i am out from Kastrup EKCH goeing to Stuttgart EDDS beeing at Flightlevel 35000 feet now and had a beautiful climb just to say so fully with aero943 !!

Wonderful work on your flightdynamics - superb !

If seeing that ( again ) i can not belive a developer who earns money put out a plane with sutch a messy flightdynamic - for me not to understand ..  🤔

You should sell this on to him ( the developer ) 😊

 

Great work, thanks for offer this to us !

 

cheers 😉

Working great  here also. Thanks for your work and time, it has made a real difference.

 

OMIGOD, this thread is Avsim at its finest. I mean, there is 60 page thread on this addon where everyone and their grandmother offered an opinion. There are youtube videos. There is a long thread about the BREDOK 737 Max over on the official MSFS forums. 

If you're still on the fence as to what this addon does or does not do, then I don't know what to say. 

And thanks to the guy who released an updated .cfg file. 

On simmarket the product sits at number 3 on the list of bestselling MSFS apps, has 58 reviews and an average rating of 4/5.

 

Edited April 7, 20215 yr by Ricardo41

1 hour ago, Ricardo41 said:

OMIGOD, this thread is Avsim at its finest. I mean, there is 60 page thread on this addon where everyone and their grandmother offered an opinion. There are youtube videos. There is a long thread about the BREDOK 737 Max over on the official MSFS forums.

Well that's true, but this is a forum where people are supposed to chat about stuff. Would you rather we all just signed in to Avsim and sat there in brooding silence? 🤣

Edited April 7, 20215 yr by Chock

1 hour ago, Chock said:

Well that's true, but this is a forum where people are supposed to chat about stuff. Would you rather we all just signed in to Avsim and sat there in brooding silence? 🤣

Exactly.

Some people can't seem to handle any talk, information, or opinion of any kind, and seem to despise it if anyone mentions anything different to their opinion, or if it goes on for more than a page or two.  Why don't they just skip over it then?  They are not being forced to read it.  I tell you why - their egos can't stop them from the constant sniping.

Well the people that want to shut down discussion that doesn't adhere to their personal opinion won't stop me anytime soon. 😝  [ Tip: Use the ignore button if you can't handle it - sad if you have to do that though to get through the day!] 

By the way, I will be trying the new config file for this 737 tonight.  I have paid more for other an add-ons and used them less.   

@tod Thanks for your work on this!

Edited April 7, 20215 yr by bobcat999

Anyone know why I don’t see other 737s in multiplayer flight?  They are invisible? only their tags show up?