Spitfire SFM (DCS: Spitfire LF Mk. IX)

    -- SFM Data
    SFM_Data = {
        aerodynamics = { -- Cx = Cx_0 + Cy^2*B2 +Cy^4*B4
            Cy0         = 0.1, -- zero AoA lift coefficient
            Mzalfa      = 4.355, -- coefficients for pitch agility
            Mzalfadt    = 0.8, -- coefficients for pitch agility
            kjx         = 2.25,
            kjz         = 0.00125,
            Czbe        = -0.016, -- coefficient, along Z axis (perpendicular), affects yaw, negative value means force orientation in FC coordinate system
            cx_gear     = 0.0277, -- coefficient, drag, gear
            cx_flap     = 0.095, -- coefficient, drag, full flaps
            cy_flap     = 0.45, -- coefficient, normal force, lift, flaps
            cx_brk      = 0.06, -- coefficient, drag, breaks
            table_data  =
            {   --      M       Cx0         Cya         B       B4      Omxmax  Aldop       Cymax
                    {   0.0,    0.0242, 0.0780,     0.0634,     0.0,    0.15,   20.0,       1.58,   },
                    {   0.2,    0.0242, 0.0780,     0.0634,     0.0,    1.606,  20.0,       1.58,   },
                    {   0.342,  0.0245, 0.0787,     0.061,      0.017,  2.353,  18.0,       1.3,    },
                    {   0.5,    0.0263, 0.0770,     0.057,      0.025,  1.145,  16.0,       0.95,   },
                    {   0.59,   0.0268, 0.0768,     0.0514,     0.026,  0.761,  15.0,       0.75,   },
                    {   0.67,   0.0331, 0.0784,     0.047,      0.021,  0.384,  14.5,       0.62,   },
                    {   0.74,   0.0465, 0.0848,     0.08,       0.16,   0.206,  10.0,       0.46,   },
                    {   0.76,   0.0527, 0.0813,     0.1,        0.25,   0.133,  9.0,        0.42,   },
                    {   0.8,    0.0737, 0.0695,     0.2,        0.36,   0.077,  6.0,        0.38,   },
                    {   0.83,   0.1006, 0.0993,     0.34,       2.4,    0.063,  4.5,        0.3,    },
                    {   0.9,    0.1470, 0.073,      0.56,       3.0,    0.042,  3.0,        0.2,    },
                }, -- end of table_data
            -- M - Mach number
            -- Cx0 - Coefficient, drag, profile, of the airplane
            -- Cya - Normal force coefficient of the wing and body of the aircraft in the normal direction to that of flight. Inversely proportional to the available G-loading at any Mach value. (lower the Cya value, higher G available) per 1 degree AOA
            -- B - Polar quad coeff
            -- B4 - Polar 4th power coeff
            -- Omxmax - roll rate, rad/s
            -- Aldop - Alfadop Max AOA at current M - departure threshold
            -- Cymax - Coefficient, lift, maximum possible (ignores other calculations if current Cy > Cymax)
        }, -- end of aerodynamics
        engine = {
            Nominal_RPM = 3000.0,
            Nmg     = 20.5, -- RPM at idle
            MinRUD  = 0, -- Min state of the throttle
            MaxRUD  = 1, -- Max state of the throttle
            MaksRUD = 1, -- Military power state of the throttle
            ForsRUD = 1, -- Afterburner state of the throttle
            type    = "Piston",

            hMaxEng = 12.5, -- Max altitude for safe engine operation in km
            dcx_eng = 0.015, -- Engine drag coeficient
            cemax   = 0.37, -- not used for fuel calulation , only for AI routines to check flight time ( fuel calculation algorithm is built in )
            cefor   = 0.37, -- not used for fuel calulation , only for AI routines to check flight time ( fuel calculation algorithm is built in )
            dpdh_m  = 1800, -- altitude coefficient for max thrust
            dpdh_f  = 1800, -- altitude coefficient for AB thrust
            k_adiab_1           = 0.037923,
            k_adiab_2           = 0.0562,
            MAX_Manifold_P_1    = 155774,
            MAX_Manifold_P_2    = 206570,
            MAX_Manifold_P_3    = 226648,
            k_after_cool        = 0.54,
            Displ               = 27,
            k_Eps               = 6,
            Stroke              = 0.152,
            V_pist_0            = 12,
            Nu_0                = 1.2,
            Nu_1                = 0.9,
            Nu_2                = 0.001,
            N_indic_0           = 1023040,
            N_fr_0              = 0.072,
            N_fr_1              = 0.02,
            Init_Mom            = 220,
            D_prop              = 3.28,
            MOI_prop            = 65,
            k_gearbox           = 2.096,
            P_oil               = 495438,
            k_boost             = 3,
            k_cfug              = 0.003,
            k_oil               = 0.00004,
            k_piston            = 3000,
            k_reg               = 0.003,
            k_vel               = 0.017,
            table_data =
            {
            --   M          Pmax
                {0.0,       16620.0},
                {0.1,       15600.0},
                {0.2,       14340.0},
                {0.3,       13320.0},
                {0.4,       12230.0},
                {0.5,       11300.0},
                {0.6,       10600.0},
                {0.7,       10050.0},
                {0.8,        9820.0},
                {0.9,        5902.0},
                {1.9,        3469.0}
            },
            -- M - Mach number
            -- Pmax - Engine thrust at military power
            -- Pfor - Engine thrust at AFB
            --cylinder_firing_order = {1,3,4,2},
        }, -- end of engine
    },