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A subsonic airfoil with high lift-to-drag ratio

A high lift-to-drag ratio, subsonic technology, applied in the wing shape and other directions, can solve the problems of large trim resistance, large bow moment coefficient, etc.

Inactive Publication Date: 2016-04-20
HARBIN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The above-mentioned high-lift airfoils have relatively large rear loads, that is, large nose-down moment coefficients, which will generate large trim resistances in applications. In addition, their lift-to-drag ratios also have large room for improvement

Method used

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  • A subsonic airfoil with high lift-to-drag ratio
  • A subsonic airfoil with high lift-to-drag ratio
  • A subsonic airfoil with high lift-to-drag ratio

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Experimental program
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Embodiment Construction

[0017] A subsonic airfoil with high lift-to-drag ratio, the geometric data points of this airfoil are as follows:

[0018]

[0019]

[0020] It is shown by calculation that the aerodynamic performance of the airfoil of the present invention has reached the design index, and its resistance divergence Mach number is greater than 0.65. In the design state, its comparison with the MS(1)-0317 airfoil is shown in Table 1.

[0021] Table 1 Comparison of aerodynamic characteristics between this airfoil and MS(1)-0317

[0022] Airfoil

[0023] This airfoil

[0024] In the table, K0.4 is the lift-to-drag ratio when the lift coefficient is 0.4, K1 is the lift-to-drag ratio when the lift coefficient is 1.0, Cm0 is the zero-lift moment coefficient, Cymax is the maximum lift coefficient, and αCymax is the stall angle of attack.

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Abstract

The invention belongs to the technical field of plane airfoil design and particularly relates to a subsonic-speed airfoil. On the premise of ensuring that the drag divergence mach number is not lower than 0.65 and the relative thickness and the trailing edge thickness are not obviously reduced, compared with the existing internationally disclosed moderate-speed high lift airfoil MS (1)-0317, in the design state of the project, the pneumatic properties of the airfoil which is invented by the project are improved as follows: 1, the lift-drag ratio in a cruising state is increased by 9%; 2, the lift-drag ratio in a climb state is increased by 16.5%; 3, the absolute value of a zero-lift moment coefficient is reduced by 21%.

Description

technical field [0001] The invention belongs to the technical field of aircraft airfoil design, in particular to a subsonic airfoil. Background technique [0002] The application target of the present invention is the wing of a subsonic general-purpose aircraft. At present, most of the airfoils used in the wings of domestic aircraft are high-lift airfoils, such as LS(1)-series airfoils and MS(1)-series airfoils. The above-mentioned high-lift airfoils all have larger afterloads, that is, larger nose-down moment coefficients, which will generate larger trim resistances in applications. In addition, their lift-to-drag ratios also have larger room for improvement. Under the design state and index requirements of the present invention, it is the first time in China to carry out a new design on the basis of the MS(1)-0317 airfoil. [0003] In the design state, the Reynolds number is 16e6 and the Mach number is 0.25. According to the requirements of the pre-research aircraft proj...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C3/10
Inventor 乔伟王洪伟
Owner HARBIN