TABLE OF CONTENTS | a | =speed of sound, Eq. 2.35; acceleration | |
| a n | = normal acceleration | |
| a t | = tangential acceleration | |
| A | = wing area; disk area | |
| A b | = cross-sectional area of the aircraft | |
| A c | = cross-sectional area of an airfoil | |
| A j | = engine nozzle area | |
| AI | = autorotation index, Eq. 14.12 | |
 | = wing aspect-ratio | |
| b | = wing span | |
| bt | = moment arm of thrust asymmetry | |
| c | = wing, blade, airfoil chord | |
| c i | = constant coefficients ( i = 0, 1, 2, ) | |
| C D | = drag coefficient | |
| C D e | = drag coefficient of idle engine in flight, Eq. 10.83 | |
| C D o | = zero-lift drag coefficient | |
| C D v | = vertical drag coefficient | |
| C l | = rolling moment coefficient | |
| C l ? | = derivative of rolling moment coefficient w.r.t. side-slip angle | |
| C l ? | = derivative of rolling moment coefficient w.r.t. aileron deflection | |
| C l ? | = derivative of rolling moment coefficient w.r.t. rudder deflection | |
| C l p | = damping-in-roll coefficient, Eq. 10.65 | |
| C L | = lift coefficient | |
| C L max | = maximum lift coefficient | |
| C L ? | = lift curve slope | |
| C N ? | = derivative of yawing moment coefficient w.r.t. side-slip angle | |
| C N ? | = derivative of yawing moment coefficient w.r.t. aileron deflection | |
| C N ? | = derivative of yawing moment coefficient w.r.t. rudder deflection | |
| c |
