The Aircraft CFG FILE [WEIGHT_AND_BALANCE] Section NOTE The sign convention used for positions in this section is ... Longitudinal = positive forward Lateral = positive right Vertical = positive upward The weight-and-balance and center of gravity of your aircraft are set in this section. Here is the [WEIGHT_AND_BALANCE] section from Flerk's Corsair with comments removed ... [WEIGHT_AND_BALANCE] empty_weight = 9205 reference_datum_position = 0.0000, 0.0000, 0.0000 empty_weight_CG_position = 0, 0, 0 max_number_of_stations = 5 station_load.0 = 170, -3.0, 0.0, 3.0 ;Moments of Inertia empty_weight_pitch_MOI = 11059.0 empty_weight_roll_MOI = 7243.0 empty_weight_yaw_MOI = 14484.0 Each parameter entry is defined as follows ... empty_weight = 9205 Aircraft Gross Weight (pounds) minus usable fuel, passengers, cargo, and expendable ordnance (CFS2). If no value is specified, CFS2 uses the value previously set in the AIR file for this model. reference_datum_position = 0.0000, 0.0000, 0.0000 X, Y, Z offset (in feet) of the aircraft's reference datum from the standard Flight Simulator center point, which is on the centerline ¼ chord aft of the leading edge. By setting the Reference Datum Position, actual aircraft loading data can be used directly according to the aircraft's manufacturer. If no value is specified, CFS2 uses 0,0,0 (Flight Simulator's default center). empty_weight_CG_position = 0, 0, 0 X, Y, Z offset (in feet) of the unloaded aircraft's center of gravity from the aircraft Reference Datum Position. The basic empty weight of the aircraft is with no fuel, passengers, or baggage or ordnance loaded. max_number_of_stations = 5 Specifies the maximum number of load stations Flight Simulator will calculate when the aircraft is loaded. While this allows you to specify an unlimited number of stations, an excessively large number here results in a longer load time for the aircraft when selected, although there is no effect on real-time performance. max_number_of_stations = 50 Specifies the maximum number of load stations Flight Simulator will calculate when the aircraft is loaded. While this allows you to specify an unlimited number of stations, an excessively large number here results in a longer load time for the aircraft when selected, although there is no effect on real-time performance. station_load.0 = 170, -3.0, 0.0, 3.0 Sets the weight and position of each passenger or payload at a specified load station identified by the unique number, station_load.N, where "N" starts with "0" and continues for as many station loads as you need. The values following the equal sign are load_weight (pounds), X, Y, Z (offset in feet of the station from the aircraft Reference Datum Position. Adding stations results in a corresponding change in aircraft flight dynamics due to the increase in gross weight and moments of inertia. ;Moments of Inertia A moment of inertia (MOI) defines the mass distribution about an aircraft axis in slug-ft2. This is largely what determines the aircraft's resistance to movement about an axis. The greater the inertia, the greater the resistance. The MOI for a particular axis increases as mass increases and/or as mass is distributed further from that axis. NOTE Moments of Inertia in the CFG file are defined for the basic weight of the aircraft. The values should not account for fuel, passengers, baggage, or, in CFS2 aircraft, expendable ordnance. CFS2 determines the total MOIs with payloads within the simulation. If no MOI values are specified, CFS2 uses the values set in the AIR file for this model, located in the aircraft folder. empty_weight_pitch_MOI = 11059.0 Sets the empty weight MOI about the lateral (X) axis. empty_weight_roll_MOI = 7243.0 Sets the empty weight MOI about the longitudinal (Z) axis. empty_weight_yaw_MOI = 14484.0 Sets the empty weight MOI about the vertical (Y) axis. Without the actual engineering data for your aircraft, moments of inertia are only rough estimates at best. MOI values can be estimated with the following formula: MOI = EmptyWeight * (D^2 / K) where, for Pitch    D = Length (feet)    K = 810 for Roll    D = Wingspan (feet)    K = 1870 for Yaw    D = 0.5* (Length+Wingspan)    K = 770