Which files control the flight model?

Ive downloaded and installed the Wunderluft example aircraft, have edited quite a bit of things to find out what they do, and Ive added my own models, but I cant seem to find any files that affect the flight model. Where do I find these files? I know the "Wunderluft.lua" file lets you play around with weight and so on, but nothing very advanced, as far as I can see.

In Wunderluft.lua, line 570 starts the SFM_Data table where you can adjust the aerodynamics and engine data. It's all there...

SFM_Data = {
	aerodynamics = -- Cx = Cx_0 + Cy^2*B2 +Cy^4*B4
	{
		Cy0			=	0,      -- zero AoA lift coefficient
		Mzalfa		=	4.355,  -- coefficients for pitch agility
		Mzalfadt	=	0.8,    -- coefficients for pitch agility
		kjx			=	2.3,    
		kjz			=	0.0011, 
		Czbe		=	-0.014, -- coefficient, along Z axis (perpendicular), affects yaw, negative value means force orientation in FC coordinate system
		cx_gear		=	0.3,    -- coefficient, drag, gear
		cx_flap		=	0.08,   -- coefficient, drag, full flaps
		cy_flap		=	0.4,    -- coefficient, normal force, lift, flaps
		cx_brk		=	0.08,   -- coefficient, drag, breaks
		table_data  = 
		{	--      M		Cx0		 	Cya			B		 	B4	    	Omxmax		Aldop		Cymax
			[1] = 	{0,	0.024,	0.07,	0.075,	0.12,	0.5,											30					,	1.2},
			[2] = 	{0.2,	0.024,	0.07,	0.075,	0.12,	1.5,										30					,	1.2},
			[3] = 	{0.4,	0.024,	0.07,	0.075,	0.12,	2.5,										30					,	1.2},
			[4] = 	{0.6,	0.0239,	0.073,	0.075,	0.12,	3.5,										30					,	1.2},
			[5] = 	{0.7,	0.024,	0.076,	0.075,	0.12,	3.5,										28.666666666667		,	1.18},
			[6] = 	{0.8,	0.0235,	0.079,	0.075,	0.12,	3.5,										27.333333333333		,	1.16},
			[7] = 	{0.9,	0.025,	0.083,	0.075,	0.125,	3.5,										26					,	1.14},
			[8] = 	{1	,	0.044,	0.085,	0.14,	0.1,	3.5,										24.666666666667		,	1.12},
			[9] = 	{1.05,	0.0465,	0.0855,	0.1775,	0.125,	3.5,										24					,	1.11},
			[10] = 	{1.1,	0.049,	0.086,	0.215,	0.15,	3.15,										18			,	1.1},
			[11] = 	{1.2,	0.049,	0.083,	0.228,	0.17,	2.45,										17,	1.05},
			[12] = 	{1.3,	0.049,	0.077,	0.237,	0.2,	1.75,										16,	1},
			[13] = 	{1.5,	0.0475,	0.062,	0.251,	0.2,	1.5,										13,	0.9},
			[14] = 	{1.7,	0.045166666666667,	0.051333333333333,	0.24366666666667,	0.32,	0.9,	12,	0.7},
			[15] = 	{1.8,	0.044,	0.046,	0.24,	0.38,	0.86,										11.4,	0.64},
			[16] = 	{2,	0.043,	0.039,	0.222,	2.5,	0.78,											10.2,	0.52},
			[17] = 	{2.2,	0.041,	0.034,	0.227,	3.2,	0.7,										9,	0.4},
			[18] = 	{2.5,	0.04,	0.033,	0.25,	4.5,	0.7,										9,	0.4},
			[19] = 	{3.9,	0.035,	0.033,	0.35,	6,		0.7,										9,	0.4},
		}, -- 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 = 
	{
		Nmg	=	62, -- RPM at idle
		MinRUD	=	0, -- Min state of the throttle
		MaxRUD	=	1, -- Max state of the throttle
		MaksRUD	=	0.85, -- Military power state of the throttle
		ForsRUD	=	0.91, -- Afterburner state of the throttle
		typeng	=	1,
		--[[
			E_TURBOJET = 0
			E_TURBOJET_AB = 1
			E_PISTON = 2
			E_TURBOPROP = 3
			E_TURBOFAN				= 4
			E_TURBOSHAFT = 5
		--]]
		
		hMaxEng	=	19, -- Max altitude for safe engine operation in km
		dcx_eng	=	0.0124, -- Engine drag coeficient
		cemax	=	1.24, -- not used for fuel calulation , only for AI routines to check flight time ( fuel calculation algorithm is built in )
		cefor	=	2.56, -- not used for fuel calulation , only for AI routines to check flight time ( fuel calculation algorithm is built in )
		dpdh_m	=	2000, --  altitude coefficient for max thrust
		dpdh_f	=	4200,  --  altitude coefficient for AB thrust
		table_data = 
		{		--   M		Pmax		 Pfor	
			[1] = 	{0,	88000,	141000},
			[2] = 	{0.2,	80000,	143000},
			[3] = 	{0.4,	79000,	150000},
			[4] = 	{0.6,	82000,	165000},
			[5] = 	{0.7,	90000,	177000},
			[6] = 	{0.8,	94000,	193000},
			[7] = 	{0.9,	96000,	200000},
			[8] = 	{1,	100000,	205000},
			[9] = 	{1.1,	100000,	214000},
			[10] = 	{1.2,	98000,	222000},
			[11] = 	{1.3,	100000,	235000},
			[12] = 	{1.5,	98000,	258000},
			[13] = 	{1.8,	94000,	276000},
			[14] = 	{2,	88000,	283000},
			[15] = 	{2.2,	82000,	285000},
			[16] = 	{2.5,	80000,	287000},
			[17] = 	{3.9,	50000,	200000},
		}, -- end of table_data
		-- M - Mach number
		-- Pmax - Engine thrust at military power
		-- Pfor - Engine thrust at AFB
	}, -- end of engine
},

How could I miss that? Thanks Blaze, let the experiments begin :)