KR-20260064233-A - Wing cross-section structure for improving lift

Abstract

A wing cross-sectional structure for improving lift is disclosed. The wing cross-sectional structure includes a trailing part located in a first direction relative to the maximum width position of the wing cross-section; and a leading part located in a second direction opposite to the first direction relative to the maximum width position, wherein the cross-sectional shape of the trailing part is formed based on a Bezier curve drawn with nondimensionalized design information based on three or more control points, and the design information defining constraint information for each control point for drawing the Bezier curve includes a relative position (x k ) on the x-axis of each control point for defining the horizontal spacing between control points, an inclination angle (θ k ) of a straight line connecting adjacent control points, and a height (h) relative to a fore-and-aft center plane for a control point set as the trailing edge of the wing.

Inventors

• 김기범
• 양희준

Assignees

• 삼성중공업 주식회사

Dates

Publication Date

20260507

Application Date

20241031

Claims (6)

1. A trailing part located in a first direction based on the maximum width position of the wing cross-section; and It includes a leading part located in a second direction which is the reverse direction of the first direction based on the maximum width position above, The cross-sectional shape of the above-mentioned trailing part is formed based on a Bezier curve represented by dimensionless design information based on three or more control points, and A wing cross-section structure for lifting enhancement, wherein the design information defining constraint information for each of the control points for illustrating the above-mentioned Bezier curve includes the relative position (x k ) of each control point on the x-axis for defining the horizontal spacing between control points, the inclination angle (θ k ) of a straight line connecting adjacent control points, and the height (h) relative to the fore-and-aft center plane for a control point set as the trailing edge of the wing.
2. In paragraph 1, In order to extend the area of the maximum width position by a predetermined width length between the trailing part and the leading part, the trailing part and the leading part are connected by a straight line with a slope of 0 for a predetermined length, A wing cross-sectional structure for lifting enhancement, wherein the cross-sectional shape of the above-mentioned leading part is formed as a NACA 00 series cross-sectional shape.
3. In paragraph 2, The above wing is a wing cross-sectional structure for enhancing lift, wherein the cross-sectional shape of the trailing part and the leading part forms a symmetrical airfoil shape that is mirrored with respect to the front-rear center plane.
4. In paragraph 1, A wing cross-sectional structure for lifting enhancement, wherein when the thickness of the trailing edge of the wing to be manufactured is determined, the relative position on the x-axis of each control point is adjusted by comparing the height (h) of the control point set as the trailing edge in the design information with the determined thickness, and after the position of each control point is determined by referring to the inclination angle of adjacent control points, a Bezier curve is generated to define the cross-sectional shape of the trailing part.
5. In paragraph 1, When there are 7 control points for illustrating a Bézier curve that defines the cross-sectional shape of one side of the trailing part based on the above-mentioned front-rear center plane, and the height (h) of the control point set as the rear edge is 0.054, design information for each of the control points that causes the cross-sectional shape of one side of the trailing part to be nondimensionalized to a range from 0 to 1 in the front-rear direction, A wing cross-section structure for enhancing lift, defined as such.
6. In paragraph 1, The above wing is a wing cross-sectional structure for enhancing lift, which is one or more of a rudder, a wing sail as a wind power assist device, and a wind blade of a wind turbine.

Description

Wing cross-section structure for improving lift The present invention relates to a wing cross-sectional structure for improving lift. The rudder, installed at the bottom of the hull or aft of the propeller, rotates to the port or starboard side to generate lift for the vessel's turning. The rudder must be able to generate high lift during turning while minimizing fluid resistance, thereby demonstrating good turning maneuverability. A high-lift rudder that generates high lift is a fish-tail rudder. Referring to FIG. 1, the fish-tail rudder (10) has a shape in which the width of the body gradually increases from the leading edge (11) to the maximum width position (w1) so as to resemble the cross-sectional shape of a fish's tail, then gradually decreases to the minimum width position (w3) at the rear, and then gradually increases from the minimum width position (w3) to the trailing edge (12). Here, the width (w2) of the trailing edge (12) is about 30% of the width length of the maximum width position (w1), and the distance (C1) from the leading edge (11) to the minimum width position (w3) is about 80% of the total length (C) of the rudder. The fishtail rudder (10) has the advantage of increasing lift by about 20% to 30% compared to NACA (National Advisory Committee for Aeronautics) series rudders, where the pressure difference of the fluid flowing on both sides of the tail section increases when the rudder is rotated to turn the ship, thereby maintaining the streamlined shape of the tail section. However, the fishtail rudder (10) has a problem in that the width (w2) of the trailing edge (12) is large enough to be about 30% of the width of the maximum width position (w1), so when the ship moves in a straight line, the resistance to the fluid becomes greater than that of a NACA series rudder, and this causes a decrease in the ship's propulsion performance. In addition, recently, in order to respond to marine environmental regulations and reduce the use of fossil fuels on ships, the installation of wind-assisted devices such as wing sails on ships is being considered. Wing sails are manufactured in the shape of airfoils and installed on ships, and they are rotated appropriately to generate lift when wind blows toward the ship. Generally, the shape of a wing, such as a rudder, wing sail, or wind turbine blade installed to generate lift on a ship, is provided as a dimensionless offset or replaced only by a conceptual description. In this case, when manufacturing the actual wing, a dimensionless offset is scaled up to the required production size; however, due to issues such as manufacturing conditions, parts of the shape may be additionally modified, such as increasing the thickness of the tail section or certain sections. In such cases, not only are the hydrodynamic properties of the wing shape defined by the offset altered, but problems also arise, such as reduced precision due to the insufficient number of offsets or deformation of the smooth curve shape. The matters described in the technical background section of this invention are for the purpose of understanding the background of the invention and cannot be concluded as prior art already known to a person with ordinary knowledge in the field to which this technology belongs. FIG. 1 is a drawing illustrating the cross-sectional shape of a fishtail rudder according to the prior art. FIG. 2 is a drawing illustrating a ship equipped with a wing sail. FIG. 3 is a diagram showing the concept of thrust, side force, and lift generation of a wing sail. FIG. 4 is a drawing illustrating a wing cross-sectional structure generated using an n-th order Bézier curve according to an embodiment of the present invention. FIG. 5 is a drawing illustrating a trailing part of a wing shaped as a Bezier curve having 7 control points according to an embodiment of the present invention. The present invention is capable of various modifications and may have various embodiments, and specific embodiments are illustrated in the drawings and described in detail in the detailed description. However, this is not intended to limit the invention to specific embodiments, and it should be understood that the invention includes all modifications, equivalents, and substitutions that fall within the spirit and scope of the invention. Embodiments of the present invention will be described below with reference to the accompanying drawings. In the accompanying drawings, identical components are given the same reference numerals, and in the description of the embodiments, identical or corresponding components may be briefly described or redundant descriptions may be omitted. In the drawings, each component may be depicted in an exaggerated size for convenience of explanation and understanding, and it is obvious that the present invention is not limited to the size and proportion of the components depicted in the drawings. FIG. 2 is a drawing illustrating a ship equipped with a wing sail, and FIG. 3 is