Reference_datum_position = 0, 0, 0 Position of reference datum relative to FS(0,0,0) (FEET), z, x, yĮmpty_weight_CG_position = 10, 0, 0.2 Position of airplane empty weight CG relative to reference datum (FEET), z, x, yĬG_forward_limit = 0.145 Gravity center forward limit (longitudinal offset) for longitudinal stabilityĬG_aft_limit = 0.28 Gravity center after limit (longitudinal offset z) w.r.t reference datum for longitudinal stability (FEET)Įmpty_weight_pitch_MOI = 69403 Empty pitch moment of inertia, Jxx (SLUG SQ FEET)Įmpty_weight_roll_MOI = 13434 Empty roll moment of inertia, Jzz (SLUG SQ FEET)Įmpty_weight_yaw_MOI = 75997 Empty yaw moment of inertia, Jyy (SLUG SQ FEET)Įmpty_weight_coupled_MOI = 100 Empty transverse moment of inertia, Jyz (SLUG SQ FEET)Īctivate_mach_limit_based_on_cg = 0 Activate mach limitation depending on CG position (true if > 0 /false othewise). Max_gross_weight = 83500 Empty weight, (LBS)Įmpty_weight = 43340 Empty weight, (LBS)
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