I've been working on a test concept for converting a DC-4 to a turboprop engine. I've tried everything I can think of but the engine will not run when I change the engine type in the aircraft.cfg file. [GeneralEngineData] engine_type=5 Engine.0=9,-26,-1.25 Engine.1=10.83,-12.33,-1.25 Engine.2=10.83,12.33,-1.25 Engine.3=9,26,-1.25 fuel_flow_scalar=1.0 min_throttle_limit=-0.499939 [TurbineEngineData] fuel_flow_gain=0.014 //Gain on fuel flow inlet_area=1.180 //Square Feet, engine nacelle inlet area rated_N2_rpm=29920.000 //RPM, second stage compressor rated value static_thrust=158.000 //Lbs, max rated static thrust at Sea Level afterburner_available=0 reverser_available=0 [propeller] thrust_scalar = 1.0 //Propeller thrust scalar propeller_type = 0 //0=Constant Speed, 1=Fixed Pitch propeller_diameter = 13.1 //Propeller Diameter, (feet) propeller_blades = 3 //Number of propeller blades propeller_moi = 19 //Propeller moment of inertia beta_max = 45 //Maximum blade pitch angle for constant speed prop, (degrees) beta_min = 15.6 //Minimum blade pitch angle for constant speed prop, (degrees) min_gov_rpm = 25520 //Miminum governed RPM prop_tc = 0.004 //Prop time-constant gear_reduction_ratio = 17.4 //Propeller gear reduction ratio fixed_pitch_beta = 0 //Fixed pitch angle of fixed pitch prop, (degrees) low_speed_theory_limit = 80 //Speed at which low speed theory becomes blended in (feet/second) prop_sync_available = 0 //Prop synchronization available? 0=FALSE, 1=TRUE prop_deice_available = 1 //Prop de-icing available? 0=FALSE, 1=TRUE prop_feathering_available= 1 //Prop feathering available? 0=FALSE, 1=TRUE prop_auto_feathering_available= 1 //Prop auto-feathering available? 0=FALSE, 1=TRUE min_rpm_for_feather = 700 //Minimum RPM for prop feathering beta_feather = 88.0 //Feathering pitch angle (degrees) power_absorbed_cf = 0.9 //Coefficient of friction for power absorbed by propeller defeathering_accumulators_available= 0 //Defeathering accumulators available? 0=FALSE, 1=TRUE prop_reverse_available = 1 //Prop reverse available? 0=FALSE, 1=TRUE minimum_on_ground_beta = 1.0 //Miminum pitch angle on ground, (degrees) minimum_reverse_beta = -14.0 //Minimum pitch angle in reverse, (degrees) [turboprop_engine] power_scalar=1.0 //Scalar on Turboprop power maximum_torque=4860.000 //max take-off rating is 4860 ft-lb at 1210 RPM [fuel] LeftMain =0,-15,0,2080,0 RightMain=0, 15,0,2080,0 fuel_type=2.000000 number_of_tank_selectors=1 electric_pump=1 Listed above is the code I used. What did I do wrong, or am I simply attempting the impossible.

Not sure, but in this case the .air file might override the cfg. Try also changing the engine type in the .air file. or better still, use a turboprop .air file.

Hi, at the moment i'm editing a aircraft.cfg file. and my problem is the moment of inertia calculation. Plane is a Comco Ikarus C42 B empty weight = 622.365 lbs length = 20.50525 ft Microsoft gives me that formula to calculate it. MOI = EmptyWeight * (D^2 / K) would mean MOI = MOI = 622.365lbs * (20.50525ft^2 / K???) what the hell is K??? i searched google but it didn't realy help me. Could someone explain "K" for dummies? thank you

The FSX SDK tells you what "K" is. It is a constant that they have defined as: Code: Pitch Roll Yaw K = 810 1870 770 Note that there are three different MOI's defined: empty_weight_pitch_moi empty_weight_roll_moi empty_weight_yaw_moi So, whichever MOI you are calculating, use the constant they've suggested!