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Corrugated airfoil profile for aircraft and optimal design method thereof

An optimized design and corrugated technology, applied in computing, special data processing applications, instruments, etc., can solve problems such as the difficulty of realizing wave-like structures

Active Publication Date: 2016-07-20
浙江睿思自动化技术有限公司 +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since the inflatable aircraft is an emerging technology, and the wavy structure is difficult to achieve on the traditional metal wing, there is no structure that uses the wavy airfoil of the lower wing in the rigid wing.

Method used

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  • Corrugated airfoil profile for aircraft and optimal design method thereof
  • Corrugated airfoil profile for aircraft and optimal design method thereof
  • Corrugated airfoil profile for aircraft and optimal design method thereof

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Embodiment Construction

[0088] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. This embodiment is carried out on the premise of the technical solution of the present invention, and detailed implementation and specific operation process are given, but the protection scope of the present invention is not limited to the following embodiments.

[0089] A corrugated airfoil for aircraft is obtained by modifying the original standard airfoil. The original standard airfoil is as follows: figure 1 Shown is the airfoil with round head and pointed tail. The corrugated airfoil retains the original smooth curve of the upper airfoil of the original standard airfoil, and at the same time, the lower airfoil is reshaped into a corrugated shape. The lower airfoil modification specifically refers to: the The front and rear edge parts of the lower airfoil of the corrugated airfoil retain the curve of the original airfoil, that is, the struc...

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Abstract

The invention relates to a corrugated airfoil profile for aircraft and an optimal design method thereof. The corrugated airfoil profile is made by modifying based on an original standard airfoil profile. In addition to the middle portion of each of front and rear edge portions being a corrugation curve formed by connecting multiple corrugation segments end to end, each corrugation segment of a lower edge curve of the corrugated airfoil profile includes a peak and a trough, the corrugations of the corrugation curve are distributed evenly or distributed proportionally; even distribution of the corrugations refers to the corrugations of each corrugation segment being equal in length; proportional distribution of the corrugations refers to: corrugation length of each corrugation segment is equal to a ratio of airfoil profile thickness in the position corresponding to the corrugation segment. Compared with the prior art, the invention has the advantages that lift drag performance and structural performance of low-speed airfoil profile can be improved, structural size and weight can be reduced under same task load conditions, and fuel economy and flight performance can be improved.

Description

technical field [0001] The invention relates to an airfoil structure for an aircraft, in particular to a corrugated airfoil for an aircraft and an optimal design method thereof. Background technique [0002] In various flight states of the aircraft, the wing is the main component for the aircraft to bear the lift, while the vertical tail and the horizontal tail are the aerodynamic components for the stability and maneuverability of the aircraft. Generally, an airplane has a plane of symmetry. If a knife is cut parallel to the plane of symmetry at any position in the span of the wing, the section of the cut wing is called a wing section or airfoil. Airfoil is an important part of wing and empennage shaping, which directly affects the aerodynamic performance and flight quality of the aircraft. [0003] For different flight speeds, the airfoil shape of the wing is different, for example: [0004] For low-subsonic aircraft, in order to increase the lift coefficient, the airfoi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15
Inventor 李军朱若愚卢博威
Owner 浙江睿思自动化技术有限公司
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