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ISSN Druckformat: 1948-2590
ISSN Online: 1948-2604
IMPROVEMENT OF ROLLING ABILITY EFFICIENCY OF MANEUVERABLE FIGHTERS WITH TWIN VERTICAL TAILS AT HIGH ANGLES OF ATTACK
ABSTRAKT
From the point of view of aerodynamics it is possible to become acquainted with the causes of yawing moment onset by deflection of aircraft ailerons. It is shown that the yawing moment is formed by incremental components of aerodynamic drag and side force. The relationship between these components determines the yawing moment sign; that is, whether this moment will contribute to the development of the roll rate or to its slowing down. Elimination of the decelerating moment of the roll in the case of aileron deflection at high angles of attack is almost impossible because the reason for its appearance is objectively associated with the natural growth of the drag penalty on the flight control surface. We describe a method of improving the rolling ability of a maneuverable fighter aircraft at the high-angle-of-attack level by using the tip section of the leading-edge flap in the rolling axis. Then, using the known criterion λ2, which defines the relationship between the rolling and yawing modes of airplane control, the effectiveness of the proposed measures is estimated. Their usefulness in terms of improving the rolling ability characteristics of the aircraft is shown.