Because it involves a moving balanced surface, a stabilator can allow the pilot to generate a given pitching moment with a lower control force.
12.
The pitching moment is, by convention, considered to be positive when it acts to pitch the airfoil in the nose-up direction.
13.
Conventional cambered airfoils supported at the aerodynamic center pitch nose-down so the " pitching moment coefficient " of these airfoils is negative.
14.
Most notably, the pitching moment being zero puts a constraint on the longitudinal motion of the aircraft that can be used to determine the elevator control input.
15.
This means that any disturbance ( such as a gust ) which raises the nose produces a nose-up pitching moment which tends to raise the nose further.
16.
This is a single value of \ alpha, for a given aircraft configuration, where there is no pitching moment, i . e . a trim point.
17.
An alternative is the use of low or null pitching moment airfoils, seen for example in the Fauvel and Marske Aircraft series of sailplanes, have used it.
18.
This airfoil section was chosen because it has zero pitching moment, which thus allows moderate torsional loads despite the resulting glider's relatively large wing area of.
19.
The chord of the airfoil, to compute a pitching moment coefficient, this coefficient changes only a little over the operating range of angle of attack of the airfoil.
20.
If an aircraft is longitudinally stable, a small increase in angle of attack will cause the pitching moment on the aircraft to change so that the angle of attack decreases.
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