Wing capable of improving transonic transverse flying quality of backswept wing with sawteeth

Abstract

The invention relates to a wing capable of improving the transonic transverse flying quality of a backswept wing with sawteeth. The wing comprises an inside leading edge flap, an outside leading edge flap, an outer wing, an aileron and an inner wing, wherein the outer side of the inner wing is fixedly connected with the outer wing, the outside leading edge flap is connected to the leading edge of the outer wing, the inside leading edge flap is connected to the leading edge of the inner wing, and the rear edge of the outer wing is connected with the aileron. The wing also comprises a trapezoid wing fence, wherein the trapezoid wing fence is connected with the upper surface of the inner wing, the inside leading edge flap and the outside leading edge flap are in bevel type obtuse sawteeth transition, the obtuse sawteeth transition and the outside leading edge flap are connected together to deflect synchronously, a narrow seam is formed between the inside leading edge flap and the obtuse sawteeth transition, the front edge of the obtuse sawtheeth transition forms an acute angle with the flow incoming direction in the plane of the wing, and a trapezoid wing fence is additionally arranged on the upper surface of the inner wing of the sweptback wing aircraft after bevel type obtuse sawteeth transition, thus being favorable for eliminating the phenomenon of transonic sudden stall of the wing and improving the transonic buffeting characteristic.

Description

technical field [0001] The invention relates to an airfoil for improving the transonic lateral flight quality of a swept-back wing with serrations. Background technique [0002] The flow field of aircraft in transonic maneuvering flight is very complex, especially the interaction between vortex and shock wave has great influence on vortex break and separation. When a swept-wing aircraft with serrated leading edge maneuvers at transonic speed, the shock wave will cause the vortex of the serrated leading edge of the wing to break up, and then cause the airflow to separate. If the shock waves formed on the left and right wings are asymmetrical, the separation flow field will be asymmetrical, resulting in a rolling moment, which will cause one side of the wing to stall suddenly without warning, resulting in the phenomenon of "wing undershoot". Stability and maneuverability will be significantly reduced, which will greatly threaten flight safety. How to improve the lateral flig...

AI Technical Summary

Problems solved by technology

If the shock waves formed on the left and right wings are asymmetrical, the separation flow field will be asymmetrical, resulting in a rolling moment, which will cause one side of the wing to stall suddenly without warning, resulting in the phenomenon of "wing undershoot". Stability and maneuverability will be significantly reduced, which will greatly threaten flight safety

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