Dissymmetry of lift is the difference in lift that exists between the advancing half of the rotor disk and the retreating half. It is caused by the fact that in directional flight the aircraft relative wind is added to the rotational relative wind on the advancing blade, and subtracted on the retreating blade. The blade passing the tail and advancing around the right side of the helicopter has an increasing airspeed which reaches maximum at the 3 o'clock position. As the blade continues, the airspeed reduces to essentially rotational airspeed over the nose of the helicopter. Leaving the nose, the blade airspeed progressively decreases and reaches minimum airspeed at the 9 o'clock position. The blade airspeed then increases progressively and again reaches rotational airspeed as it passes over the tail.

Referring to the graphic, noting the reverse flow area:

Two factors, Rotor RPM and Aircraft Airspeed, control blade airspeed during flight. Both factors are variable to some degree, but must remain within certain operating limits.

Angle of attack remains as the one variable that may be used by the pilot to compensate for dissymmetry of lift.

The pitch angle of the rotor blades can be varied throughout their range, from flat pitch to the stalling pitch angle, to change angle of attack and to compensate for lift differential.

The next graphic shows the relationship between blade pitch angle and blade airspeed during forward flight:

## Dissymmetry Of Lift And The Tail Rotor

The tail rotor also experiences dissymmetry of lift during forward flight, because of its own advancing and retreating blades.

Although the plane of rotation is vertical, the effects are the same as for the main rotor in the horizontal plane. Dissymmetry is usually corrected for by a flapping hinge action.

Two basic types of flapping hinges, the Delta and Offset.
Either can be found on helicopters in the fleet.

Note that the delta hinge (b) is not oriented parallel to the blade chord, designed that way so that flapping automatically introduces cyclic feathering which corrects for dissymmetry of lift.

The offset hinge is located outboard from the hub and uses centrifugal force to produce substantial forces that act on the hub itself. One important advantage of offset hinges is the presence of control regardless of lift condition, since centrifugal force is independent of lift.