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Index to Math Model Constants

©2009 PerfectLogic Corporation, All Rights Reserved

Entries in the table below define the symbols used in the development of the mathematical model of flight dynamics.

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Constants Defined

Constant	Description	Value
	Thrust gain (See Note 1)	2.0
	Commanded thrust constant (See Note 1)	0.003
	Commanded thrust constant (See Note 1)	0.1
	Lift gain (See Note 1)	0.75
	Commanded lift constant (See Note 1)	0.01
	Commanded lift constant (See Note 1)	0.4
	Bank angle gain (See Note 1)	1.0
\n	Commanded bank angle constant (See Note 1)	0.1
	Altitude rate gain (See Note 1)	0.1
	Maximum bank angle	30.0 degrees
	Maximum allowable course change	(179/180)π radians
	Fuel consumption model constant (See Note 1)	4 x 10-6 slugs/pounds-seconds
	Drag model constant (See Note 1)	3.8173 x 10-2
	Drag model constant (See Note 1)	2.4789 x 10-2
	Lift model constant (See Note 1)	10.0
	Lift model constant (See Note 1)	0.5
	Mean gravitational acceleration	32.0878 ft/sec2
	Pi	3.141592653589793
	Eccentricity of the earth ellipsoid	0.0818191908426
	Length of earth ellipsoids semimajor axis	6,378,137.0000 meters
	Length of earth ellipsoids semiminor axis	6,356,752.3142 meters
	Mean Equatorial radius	6,378.077 nautical miles
	Sea-level air temperature (ISA)	288.150 °K
	Stratospheric isothermal temperature	216.650 °K
	Sea-level air pressure (ISA)	1.01325 N/m2
	Sea-level air density (ISA)	1.2250 kg/m3
	Sea-level gravitational acceleration (ISA)	9.78039 m/sec2
	Troposheric temperature gradient, dT/dh (ISA)	-0.0065 °K/m
	Stratospheres lower altitude limit (ISA)	11,000.0 m
	Universal gas constant for air	287.0528 Joules/kg °K
	Specific heat ratio for air (ISA)	1.4
	Speed of sound at sea-level (ISA)	340.294 meters/sec
	Feet per nautical mile	6,076.1155 ft/n.mi.
	Nautical mile per foot	1.64578833 x 10-4 n.mi./ft.
	Meters per nautical mile	1,852.0 meters/n.mi.
	Nautical miles per meter	5.39956803 x 10-4 n.mi./meter

Note 1 - These are nominal values; these constants are not appropriate for all aircraft. Values determining desired behavior may need to adjusted experimentally or estimated from aircraft characteristics.

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© 2009 PerfectLogic Corporation