A_{th} |
= | Throttle plate open area |

b |
= | Wingspan |

c |
= | Length of mean aerodynamic chord |

[C] |
= | Direction cosine matrix representing aircraft orientation |

C_{ij} |
= | Components of the direction cosine matrix |

C_{D} |
= | Discharge coefficient of the engine throttle |

C_{T} |
= | Propeller coefficient of thrust |

C_{P} |
= | Propeller coefficient of power required |

C_{X}, C_{Y}, etc. |
= | Nondimensional force and moment coefficients |

= | Stability derivatives and/or polynomial coefficients | |

D |
= | Propeller diameter |

e_{0}, e_{1}, e_{2}, e_{3} |
= | Quarternions representing aircraft orientation |

F_{f} |
= | Forward friction force exerted on a landing gear tire |

F_{n} |
= | Ground normal force exerted on a landing gear tire |

F_{s} |
= | Sideward friction force exerted on a landing gear tire |

(F/A) |
= | Fuel to air mixture ratio |

g |
= | Acceleration of gravity ft/s |

h |
= | Altitude |

h |
= | Distance from the ground |

I_{p} |
= | Propeller polar moment of inertia |

I_{xx}, I_{yy}, I_{zz} |
= | Aircraft moments of inertia |

I_{xy}, I_{xz}, I_{yz} |
= | Aircraft products of inertia |

J |
= | Propeller advance ratio |

L, M, N |
= | Components of the resultant moment on the airplane |

m |
= | Mass of the airplane |

m_{f} |
= | Fuel mass |

= | Mass flow rate past the throttle | |

M |
= | Mach number |

N |
= | Propeller/engine angular speed, revolutions per second |

p |
= | Outside air pressure |

p_{m} |
= | Manifold pressure |

P |
= | Power required by propeller |

P_{e} |
= | Excess power delivered to the propeller |

p, q, r |
= | Components of aircraft angular velocity |

= | Nondimensional components of aircraft angular velocity | |

q |
= | Dynamic pressure |

Q_{p} |
= | Resultant torque on the propeller |

r |
= | Distance from the Earth's center |

R |
= | Gas constant of the air (ft lb)/(slug R) |

S |
= | Wing planform area |

T |
= | Thrust force |

T |
= | Outside air temperature |

T_{m} |
= | Manifold temperature |

u, v, w |
= | Components of aircraft velocity |

u_{a}, v_{a}, w_{a} |
= | Wind-relative components of aircraft velocity |

u_{g}, v_{g}, w_{g} |
= | Components of the velocity of a landing gear tire |

V |
= | Airspeed |

V_{k} |
= | Threshold velocity for static friction |

V_{d} |
= | Total displacement of the engine |

V_{m} |
= | Volume of the intake manifold |

X, Y, Z |
= | Components of the resultant force on the aircraft |

x, y, z |
= | Coordinates in a Cartesian coordinate system |

x_{c}, y_{c}, z_{c} |
= | Coordinates of the aircraft's CG |

x_{g}, y_{g}, z_{g} |
= | Coordinates of the bottom of an extended landing gear tire |

x_{s} |
= | Distance of the screen from user's eyes |

z_{p} |
= | Body z-coordinate of the propeller shaft |

= | Angle of attack | |

= | Angle of sideslip | |

= | Compressibility correction factor | |

= | Specific heat ratio of the air | |

= | Differential aileron deflection | |

= | Percent of full brake pressure applied | |

= | Elevator deflection | |

= | Flap deflection | |

= | Leading-edge flap deflection | |

= | Rudder deflection | |

= | Propeller efficiency | |

= | Volumetric efficiency of the engine | |

= | Pitch Euler angle | |

= | Longitude | |

= | Static and kinematic coefficients of friction of tires | |

= | Outside air density | |

= | Roll Euler angle | |

= | Geodetic latitude | |

= | Geocentric latitude | |

= | Yaw Euler angle |