Post by Tom Goodrick on Jun 12, 2011 21:38:43 GMT -5
I decided to go for a ride in my Dreamliner today. This aircraft has been in the news lately because one cause of the delay in its development has been the need to set up a plant in South Carolina (?) with no union restrictions.
I obtained a model several years ago and worked on it very briefly, just enough so I could fly it around. The model was in FSX and was by Camil Valiquette. As is typical of this designer's work, the physical depiction is excellent. The FD are not so well done.
I managed to screw up the test flight a bit. I took off and turned on the autopilot set for a turn from 180 to 165 as I adjusted the thrust, got the gear and the flaps. The full thrust used to start the take off came back to 80% and then 65% at the start of climb. The AP was set to level at 15000 ft. The rate was 1800 fpm as I reduced thrust more after seeing 200 KIAS. Flaps were zeroed. Then I noticed 3 minutes had elapsed. I made my mistake. I wanted to see what the takeoff looked like so I replayed the first 3 minutes. After the replay the aircraft was in a steady climb but when back on the autopilot. It promptly stalled and the plane did a tail slide while I switched to manual control and worked my way out of it. I lost a few thousand feet but got out of trouble and back to climbing steadily. I might have bent something during the recovery but I didn't crash.
I leveled at 15000 ft and cruise a round a little at 310 KIAS and 45% thrust. I flew a very wide rectangle around HSV (not far from CHA) and then descended for an approach from 4000 ft 15 mi north of HSV. I did not like the pitch motions after each flap adjustment and with the spoilers. That needs work.
Last time I worked on this I checked stall speeds and set the V speeds. Vref on approach for the existing weight was 120 KIAS. 45% thrust was needed with everything hanging. That worked quite well once I got on the glideslope. I turned on the landing speed gauge and used its digital FPM to come down the final glideslope at -290 fpm. I cut thrust over the numbers. The landing looked steep but worked well at 110 KIAS and -290 fpm. Weight was 544232 lb and CG was at 24.8% at 194210 lb. Aux tanks were at 32%, Mains at 90%, Center at 94%. Payload was 50,000 lbs.
Below are the major elements of the aircraft.cfg as well as some elements of the aircraft.cfg for the Boeing 777 which has very similar weight capacity and performance.
Current copy of aircraft.cfg for
Boeing Dreamliner with FD by TG
[fltsim.0]
title=Boeing 787-8 ags Northwest
sim=787-8
model=787-8 ags
[WEIGHT_AND_BALANCE]
max_gross_weight= 602973.991
empty_weight= 300000.000
reference_datum_position= 0.000, 0.000, 0.000
empty_weight_CG_position= 0.000, 0.000, 0.000
max_number_of_stations=50
station_load.0=50000.000000,0.000000,0.000000,0.000000
empty_weight_roll_MOI= 11107293.000
empty_weight_pitch_MOI= 13453416.000
empty_weight_yaw_MOI= 25014576.000
empty_weight_coupled_MOI= 0.000
[fuel]
Center1= 0.000, 0.000, 0.000, 9070.000, 0.000
LeftMain= 0.000, 0.000, 0.000, 11110.000, 0.000
LeftAux= 0.000, -83.167, 0.000, 825.000, 0.000
RightMain= 0.000, 0.000, 0.000, 11110.000, 0.000
RightAux= 0.000, 83.167, 0.000, 825.000, 0.000
fuel_type=2.000000
number_of_tank_selectors=1
electric_pump=0
[airplane_geometry]
wing_area= 5863.000
wing_span= 208.000
wing_root_chord= 28.167
wing_dihedral= 6.998
[contact_points]
point.0=1, 79.42, 0.00, -9.350, 2500.1, 0, 3.500, 50.0, 0.5, 2.5, 0.9000, 15.0,
15.0, 0, 0.0, 0.0
point.1=1, -17.50, -12.00, -11.383, 1574.8, 1, 3.167, 20.0, 1.0, 2.5, 0.8500, 15.0,
15.0, 2, 0.0, 0.0
point.2=1, -17.50, 12.00, -11.383, 1574.8, 2, 3.167, 20.0, 1.0, 2.5, 0.8500, 15.0,
15.0, 3, 0.0, 0.0
[GeneralEngineData]
engine_type = 1
Engine.0 = 10.500, -32.600, -8.400
Engine.1 = 10.500, 32.600, -8.400
fuel_flow_scalar = 0.689
min_throttle_limit=-0.150024
[TurbineEngineData]
fuel_flow_gain= 0.002
inlet_area= 101.714
rated_N2_rpm= 29920.000
static_thrust= 84761.900
afterburner_available= 0
reverser_available= 1.000
[flight_tuning]
pitch_stability=1.000
roll_stability=1.000
yaw_stability=1.000
parasite_drag_scalar=1.000
induced_drag_scalar=1.000
elevator_effectiveness=1.500
aileron_effectiveness=1.000
rudder_effectiveness=1.000
elevator_trim_effectiveness=1.000
aileron_trim_effectiveness=1.000
rudder_trim_effectiveness=1.000
[Reference Speeds]
flaps_up_stall_speed= 153.000
full_flaps_stall_speed= 93.000
cruise_speed= 500.0
max_indicated_speed=360.0
max_mach=0.899902
[flaps.0] //Inboard Trailing Edge
type = 1 // 1 - tail, 2 - lead
span-outboard = 0.2 // 0.0 .. 1.0
extending-time = 15 // seconds
flaps-position.0 = 0 // degrees
flaps-position.1 = 0 // degrees
flaps-position.2 = 5 // degrees
flaps-position.3 = 10 // degrees
flaps-position.4 = 15 // degrees
flaps-position.5 = 20 // degrees
flaps-position.6 = 30 // degrees
damaging-speed = 250 // KIAS
blowout-speed = 290 // KIAS
lift_scalar = 1.00
drag_scalar = 1.00
pitch_scalar= 1.00
system_type = 0 //Hydraulic
[flaps.1] //Outboard Trailing Edge
type = 1 // 1 - tail, 2 - lead
span-outboard = 0.8 // 0.0 .. 1.0
extending-time = 15 // seconds
flaps-position.0 = 0 // degrees
flaps-position.1 = 0 // degrees
flaps-position.2 = 5 // degrees
flaps-position.3 = 10 // degrees
flaps-position.4 = 15 // degrees
flaps-position.5 = 20 // degrees
flaps-position.6 = 30 // degrees
damaging-speed = 250 // KIAS
blowout-speed = 290 // KIAS
lift_scalar = 1.00
drag_scalar = 1.00
pitch_scalar= 1.00
system_type = 0 //Hydraulic
[flaps.2] //Inboard Leading Edge Slats
type = 2 // 1 - tail, 2 - lead
span-outboard = 0.5 // 0.0 .. 1.0
extending-time = 5 // seconds
flaps-position.0 = 0 // degrees
flaps-position.1 = 1.0 // degrees
flaps-position.2 = 1.0 // degrees
flaps-position.3 = 1.0 // degrees
flaps-position.4 = 1.0 // degrees
flaps-position.5 = 1.0 // degrees
flaps-position.6 = 1.0 // degrees
damaging-speed = 250 // KIAS
blowout-speed = 290 // KIAS
lift_scalar = 1.00
drag_scalar = 1.00
pitch_scalar= 1.00
system_type = 0 //Hydraulic
[General]
performance=This aircraft is free on the internet\nCopyright to Camil
Valiquette\nThis product could not be sold\nNO SALE PERMIT: IF YOU SEE THAT
LINE\nCamSim --- Aviation Simulation\nDesigner: Camil Valiquette\nPainter: Camil
Valiquette\nhttp:\npages.infinit.net\/camsim
Category=airplane
Below are the elements of the aircraft.cfg of the Boeing 777:
B777 data
[WEIGHT_AND_BALANCE]
max_gross_weight = 660000 // (pounds)
empty_weight = 347800 // (pounds)
reference_datum_position = 0, 0, 0 // (feet) distance from FlightSim Reference position: (1/4 chord, centerline, waterline)
empty_weight_CG_position = -12, 0, 0 // (feet) longitudinal, lateral, vertical distance from specified datum
;Moments of Inertia
empty_weight_pitch_MOI = 18000000
empty_weight_roll_MOI = 5500000
empty_weight_yaw_MOI = 16300000
empty_weight_coupled_MOI= 0.0
[airplane_geometry]
wing_area = 4605.0 //Square feet
wing_span = 200.0 //Feet
wing_root_chord = 42.0 //Feet
wing_dihedral = 6.2 //Degrees
wing_incidence = 1.0 //Degrees
wi
[GeneralEngineData]
engine_type = 1 //0=Piston, 1=Jet, 2=None, 3=Helo-Turbine, 4=Rocket, 5=Turboprop
Engine.0 = 10.5, -33.6, -6.4 //(feet) longitudinal, lateral, vertical distance from reference datum
Engine.1 = 10.5, 33.6, -6.4 //(feet) longitudinal, lateral, vertical distance from reference datum
fuel_flow_scalar = 1 //Scalar for fuel flow efficiency
min_throttle_limit = -0.25; //Minimum percent throttle. Generally negative for turbine reverser
[TurbineEngineData]
fuel_flow_gain = 0.002 //Gain on fuel flow
inlet_area = 113.0 //Square Feet, engine nacelle inlet area
rated_N2_rpm = 29920 //RPM, second stage compressor rated value
static_thrust = 84000 //Lbs, max rated static thrust at Sea Level
afterburner_available = 0 //Afterburner available?
reverser_available = 1 //Thrust reverser available?
I obtained a model several years ago and worked on it very briefly, just enough so I could fly it around. The model was in FSX and was by Camil Valiquette. As is typical of this designer's work, the physical depiction is excellent. The FD are not so well done.
I managed to screw up the test flight a bit. I took off and turned on the autopilot set for a turn from 180 to 165 as I adjusted the thrust, got the gear and the flaps. The full thrust used to start the take off came back to 80% and then 65% at the start of climb. The AP was set to level at 15000 ft. The rate was 1800 fpm as I reduced thrust more after seeing 200 KIAS. Flaps were zeroed. Then I noticed 3 minutes had elapsed. I made my mistake. I wanted to see what the takeoff looked like so I replayed the first 3 minutes. After the replay the aircraft was in a steady climb but when back on the autopilot. It promptly stalled and the plane did a tail slide while I switched to manual control and worked my way out of it. I lost a few thousand feet but got out of trouble and back to climbing steadily. I might have bent something during the recovery but I didn't crash.
I leveled at 15000 ft and cruise a round a little at 310 KIAS and 45% thrust. I flew a very wide rectangle around HSV (not far from CHA) and then descended for an approach from 4000 ft 15 mi north of HSV. I did not like the pitch motions after each flap adjustment and with the spoilers. That needs work.
Last time I worked on this I checked stall speeds and set the V speeds. Vref on approach for the existing weight was 120 KIAS. 45% thrust was needed with everything hanging. That worked quite well once I got on the glideslope. I turned on the landing speed gauge and used its digital FPM to come down the final glideslope at -290 fpm. I cut thrust over the numbers. The landing looked steep but worked well at 110 KIAS and -290 fpm. Weight was 544232 lb and CG was at 24.8% at 194210 lb. Aux tanks were at 32%, Mains at 90%, Center at 94%. Payload was 50,000 lbs.
Below are the major elements of the aircraft.cfg as well as some elements of the aircraft.cfg for the Boeing 777 which has very similar weight capacity and performance.
Current copy of aircraft.cfg for
Boeing Dreamliner with FD by TG
[fltsim.0]
title=Boeing 787-8 ags Northwest
sim=787-8
model=787-8 ags
[WEIGHT_AND_BALANCE]
max_gross_weight= 602973.991
empty_weight= 300000.000
reference_datum_position= 0.000, 0.000, 0.000
empty_weight_CG_position= 0.000, 0.000, 0.000
max_number_of_stations=50
station_load.0=50000.000000,0.000000,0.000000,0.000000
empty_weight_roll_MOI= 11107293.000
empty_weight_pitch_MOI= 13453416.000
empty_weight_yaw_MOI= 25014576.000
empty_weight_coupled_MOI= 0.000
[fuel]
Center1= 0.000, 0.000, 0.000, 9070.000, 0.000
LeftMain= 0.000, 0.000, 0.000, 11110.000, 0.000
LeftAux= 0.000, -83.167, 0.000, 825.000, 0.000
RightMain= 0.000, 0.000, 0.000, 11110.000, 0.000
RightAux= 0.000, 83.167, 0.000, 825.000, 0.000
fuel_type=2.000000
number_of_tank_selectors=1
electric_pump=0
[airplane_geometry]
wing_area= 5863.000
wing_span= 208.000
wing_root_chord= 28.167
wing_dihedral= 6.998
[contact_points]
point.0=1, 79.42, 0.00, -9.350, 2500.1, 0, 3.500, 50.0, 0.5, 2.5, 0.9000, 15.0,
15.0, 0, 0.0, 0.0
point.1=1, -17.50, -12.00, -11.383, 1574.8, 1, 3.167, 20.0, 1.0, 2.5, 0.8500, 15.0,
15.0, 2, 0.0, 0.0
point.2=1, -17.50, 12.00, -11.383, 1574.8, 2, 3.167, 20.0, 1.0, 2.5, 0.8500, 15.0,
15.0, 3, 0.0, 0.0
[GeneralEngineData]
engine_type = 1
Engine.0 = 10.500, -32.600, -8.400
Engine.1 = 10.500, 32.600, -8.400
fuel_flow_scalar = 0.689
min_throttle_limit=-0.150024
[TurbineEngineData]
fuel_flow_gain= 0.002
inlet_area= 101.714
rated_N2_rpm= 29920.000
static_thrust= 84761.900
afterburner_available= 0
reverser_available= 1.000
[flight_tuning]
pitch_stability=1.000
roll_stability=1.000
yaw_stability=1.000
parasite_drag_scalar=1.000
induced_drag_scalar=1.000
elevator_effectiveness=1.500
aileron_effectiveness=1.000
rudder_effectiveness=1.000
elevator_trim_effectiveness=1.000
aileron_trim_effectiveness=1.000
rudder_trim_effectiveness=1.000
[Reference Speeds]
flaps_up_stall_speed= 153.000
full_flaps_stall_speed= 93.000
cruise_speed= 500.0
max_indicated_speed=360.0
max_mach=0.899902
[flaps.0] //Inboard Trailing Edge
type = 1 // 1 - tail, 2 - lead
span-outboard = 0.2 // 0.0 .. 1.0
extending-time = 15 // seconds
flaps-position.0 = 0 // degrees
flaps-position.1 = 0 // degrees
flaps-position.2 = 5 // degrees
flaps-position.3 = 10 // degrees
flaps-position.4 = 15 // degrees
flaps-position.5 = 20 // degrees
flaps-position.6 = 30 // degrees
damaging-speed = 250 // KIAS
blowout-speed = 290 // KIAS
lift_scalar = 1.00
drag_scalar = 1.00
pitch_scalar= 1.00
system_type = 0 //Hydraulic
[flaps.1] //Outboard Trailing Edge
type = 1 // 1 - tail, 2 - lead
span-outboard = 0.8 // 0.0 .. 1.0
extending-time = 15 // seconds
flaps-position.0 = 0 // degrees
flaps-position.1 = 0 // degrees
flaps-position.2 = 5 // degrees
flaps-position.3 = 10 // degrees
flaps-position.4 = 15 // degrees
flaps-position.5 = 20 // degrees
flaps-position.6 = 30 // degrees
damaging-speed = 250 // KIAS
blowout-speed = 290 // KIAS
lift_scalar = 1.00
drag_scalar = 1.00
pitch_scalar= 1.00
system_type = 0 //Hydraulic
[flaps.2] //Inboard Leading Edge Slats
type = 2 // 1 - tail, 2 - lead
span-outboard = 0.5 // 0.0 .. 1.0
extending-time = 5 // seconds
flaps-position.0 = 0 // degrees
flaps-position.1 = 1.0 // degrees
flaps-position.2 = 1.0 // degrees
flaps-position.3 = 1.0 // degrees
flaps-position.4 = 1.0 // degrees
flaps-position.5 = 1.0 // degrees
flaps-position.6 = 1.0 // degrees
damaging-speed = 250 // KIAS
blowout-speed = 290 // KIAS
lift_scalar = 1.00
drag_scalar = 1.00
pitch_scalar= 1.00
system_type = 0 //Hydraulic
[General]
performance=This aircraft is free on the internet\nCopyright to Camil
Valiquette\nThis product could not be sold\nNO SALE PERMIT: IF YOU SEE THAT
LINE\nCamSim --- Aviation Simulation\nDesigner: Camil Valiquette\nPainter: Camil
Valiquette\nhttp:\npages.infinit.net\/camsim
Category=airplane
Below are the elements of the aircraft.cfg of the Boeing 777:
B777 data
[WEIGHT_AND_BALANCE]
max_gross_weight = 660000 // (pounds)
empty_weight = 347800 // (pounds)
reference_datum_position = 0, 0, 0 // (feet) distance from FlightSim Reference position: (1/4 chord, centerline, waterline)
empty_weight_CG_position = -12, 0, 0 // (feet) longitudinal, lateral, vertical distance from specified datum
;Moments of Inertia
empty_weight_pitch_MOI = 18000000
empty_weight_roll_MOI = 5500000
empty_weight_yaw_MOI = 16300000
empty_weight_coupled_MOI= 0.0
[airplane_geometry]
wing_area = 4605.0 //Square feet
wing_span = 200.0 //Feet
wing_root_chord = 42.0 //Feet
wing_dihedral = 6.2 //Degrees
wing_incidence = 1.0 //Degrees
wi
[GeneralEngineData]
engine_type = 1 //0=Piston, 1=Jet, 2=None, 3=Helo-Turbine, 4=Rocket, 5=Turboprop
Engine.0 = 10.5, -33.6, -6.4 //(feet) longitudinal, lateral, vertical distance from reference datum
Engine.1 = 10.5, 33.6, -6.4 //(feet) longitudinal, lateral, vertical distance from reference datum
fuel_flow_scalar = 1 //Scalar for fuel flow efficiency
min_throttle_limit = -0.25; //Minimum percent throttle. Generally negative for turbine reverser
[TurbineEngineData]
fuel_flow_gain = 0.002 //Gain on fuel flow
inlet_area = 113.0 //Square Feet, engine nacelle inlet area
rated_N2_rpm = 29920 //RPM, second stage compressor rated value
static_thrust = 84000 //Lbs, max rated static thrust at Sea Level
afterburner_available = 0 //Afterburner available?
reverser_available = 1 //Thrust reverser available?