Flight Measurements of the Lateral Control Characteristics of Narrow-Chord Ailerons on the Trailing Edge of a Full-Span Slotted Flap.

摘要

Results are presented of flight tests made to determine the effect of flap deflection on the lateral control characteristics of a modified Brewster F2A-2 airplane equipped with partial-span narrow-chord ailerons on the trailing edge of a full-span NACA slotted flap. The investigation included determination of the rolling and yawing characteristics of the airplane in abrupt aileron rolls with the slotted flap at various settings ranging from 0 deg. to about 40 deg. The results showed that the effectiveness of the ailerons was greatly reduced at flap deflections greater than about 20 deg. For flap deflections up to about 20 deg., the aileron effectiveness was about the same as the flaps retracted, but the adverse yawing velocity developed in the abrupt aileron rolls was somewhat increased. This increase in the adverse yawing velocity, however, was not considered objectionable by the pilot.