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The longitudinal static stability of an aircraft depends on the location of its center of gravity relative to the neutral point. As the center of gravity moves increasingly forward, the pitching moment arm is increased, increasing stability.
Stability is the ability of the aircraft to counteract disturbances to its flight path. According to David P. Davies, there are six types of aircraft stability: speed stability, stick free static longitudinal stability, static lateral stability, directional stability, oscillatory stability, and spiral stability. [5]: 164
is the static margin and must be negative for longitudinal static stability. Alternatively, positive angle of attack must generate positive yawing moment on a statically stable missile, i.e. N β {\displaystyle N_{\beta }} must be positive.
Static stability may also refer to: In aircraft or missiles: Static margin — a concept used to characterize the static stability and controllability of aircraft and missiles. Longitudinal stability — the stability of an aircraft in the longitudinal, or pitching, plane during static (established) conditions. In meteorology:
The pitching moment coefficient is important in the study of the longitudinal static stability of aircraft and missiles. The pitching moment coefficient C m {\displaystyle C_{m}} is defined as follows [ 1 ] : Section 5.4
A Boeing 737 uses an adjustable stabilizer, moved by a jackscrew, to provide the required pitch trim forces. Generic stabilizer illustrated. A horizontal stabilizer is used to maintain the aircraft in longitudinal balance, or trim: [3] it exerts a vertical force at a distance so the summation of pitch moments about the center of gravity is zero. [4]
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For longitudinal static stability: < > For directional static stability: > < Where: = + = For a force acting away from the aerodynamic center, which is away from the reference point: