a wing structure

Abstract

The invention discloses a wing structure. The wing structure consists of continuous wing profiles, wherein the spans of the wing profiles away from the root of a wing are 0 percent, 20 percent, 40 percent, 60 percent, 80 percent and 100 percent respectively; the ratio of wingspan to chord length is 5.50-7.24; the leading edge of the wing is a high-order curved line of an approximately parabolic shape; the maximum relative curvature of each wing profile is 7.5 percent and is positioned at a position at 17-33 percent of the chord length; the maximum relative thickness of each wing profile is 13.1 percent and is positioned at a position at 11-24 percent of the chord length; the curvature and the thickness of each wing profile tend to be increased and then decreased along the corresponding span. Compared with a parametrically-similar NACA (national advisory committee for aeronautics) 4-digit wing profile, the wing structure has the advantages that a low-speed lift coefficient is large, a resistance coefficient is small, and a large angle of stall is formed; under the condition of same flight parameters, according to the wing structure, the flight noise is low, and the lift coefficient is relatively large when an angle of attack is 25 degrees, and slowly declines when the angle of attack is greater than 25 degrees.

Description

technical field [0001] The invention relates to a wing structure of an aircraft. technical background [0002] Gliders, seaplanes, model planes, unmanned aerial vehicles and other models require wings with a high lift coefficient to facilitate take-off due to low power or no power. In the cruising stage, in order to increase the range, the wings are required to have a higher lift coefficient and a lower drag coefficient. UAVs often need to perform special tasks such as reconnaissance. After entering the reconnaissance area, they often need to turn off the power gliding flight, which requires the wings to have a high lift coefficient and low flight noise. [0003] In the prior art, NACA 4-digit series airfoils are often used, and this series of airfoils is suitable for propeller aircraft flying at relatively low speeds. [0004] However, the aerodynamic performance of this series of airfoils is not ideal and cannot meet some special needs. Especially stall angle and flight...

AI Technical Summary

Problems solved by technology

[0004] However, the aerodynamic performance of this series of airfoils is not ideal and cannot meet some special needs

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