15-12-2014, 10:40 AM
Thank you guys for this forum so much! I finally have some numbers that work very well for me, hope they help you as well.
Flight Plan:
Distance: 913.6 Nm
Estimated fuel burn: 15,140 lb
Alt: FL 220
Speed: 315 knots
Actual numbers after the flight:
Distance: 914 Nm
Fuel burn: 16,157
Numbers:
[GeneralEngineData]
engine_type = 1 //0=Piston, 1=Jet, 2=None, 3=Helo-Turbine, 4=Rocket, 5=Turboprop
Engine.0 = 0, -16.1, -3.2 //(feet) longitudinal, lateral, vertical distance from reference datum
Engine.1 = 0, 16.1, -3.2 //(feet) longitudinal, lateral, vertical distance from reference datum
fuel_flow_scalar = 0.7 //Scalar for fuel flow efficiency
min_throttle_limit = -0.25 //Minimum percent throttle. Generally negative for turbine reverser
max_contrail_temperature = -30 //Temperature (deg C) below which contrails may appear
[TurbineEngineData]
fuel_flow_gain = 0.002 //Gain on fuel flow
inlet_area = 19.6 //Square Feet, engine nacelle inlet area
rated_N2_rpm = 29920 //RPM, second stage compressor rated value
static_thrust = 24200 //Lbs, max rated static thrust at Sea Level
afterburner_available = 0 //Afterburner available?
reverser_available = 1 //Thrust reverser available?
ThrustSpecificFuelConsumption = 0.45 //Thrust specific fuel consumption (Jets)
AfterBurnThrustSpecificFuelConsumption = 0 //TSFC with afterburn/reheat engaged
Flight Plan:
Distance: 913.6 Nm
Estimated fuel burn: 15,140 lb
Alt: FL 220
Speed: 315 knots
Actual numbers after the flight:
Distance: 914 Nm
Fuel burn: 16,157
Numbers:

[GeneralEngineData]
engine_type = 1 //0=Piston, 1=Jet, 2=None, 3=Helo-Turbine, 4=Rocket, 5=Turboprop
Engine.0 = 0, -16.1, -3.2 //(feet) longitudinal, lateral, vertical distance from reference datum
Engine.1 = 0, 16.1, -3.2 //(feet) longitudinal, lateral, vertical distance from reference datum
fuel_flow_scalar = 0.7 //Scalar for fuel flow efficiency
min_throttle_limit = -0.25 //Minimum percent throttle. Generally negative for turbine reverser
max_contrail_temperature = -30 //Temperature (deg C) below which contrails may appear
[TurbineEngineData]
fuel_flow_gain = 0.002 //Gain on fuel flow
inlet_area = 19.6 //Square Feet, engine nacelle inlet area
rated_N2_rpm = 29920 //RPM, second stage compressor rated value
static_thrust = 24200 //Lbs, max rated static thrust at Sea Level
afterburner_available = 0 //Afterburner available?
reverser_available = 1 //Thrust reverser available?
ThrustSpecificFuelConsumption = 0.45 //Thrust specific fuel consumption (Jets)
AfterBurnThrustSpecificFuelConsumption = 0 //TSFC with afterburn/reheat engaged