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Aircraft wind tunnel support interference correction method

An interference correction and aircraft technology, applied in the aviation field, can solve problems such as tail support interference, body shape after damage, and interference amount is difficult to deduct, so as to achieve the effect of improving accuracy

Active Publication Date: 2021-09-24
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, for high-stealth aircraft, the rear body is flat, and the tail support will destroy the rear body shape, introducing rear body shape distortion and tail support interference, and the amount of interference is not easy to deduct

Method used

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  • Aircraft wind tunnel support interference correction method
  • Aircraft wind tunnel support interference correction method
  • Aircraft wind tunnel support interference correction method

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Embodiment Construction

[0039] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The invention belongs to the technical field of aviation, and particularly relates to an aircraft wind tunnel support interference correction method. The method comprises the steps of 1, obtaining airplane models including a first airplane model, a second airplane model, a third airplane model and a fourth airplane model; and 2, under the same working condition, performing a wind tunnel test on the first airplane model, the second airplane model, the third airplane model and the fourth airplane model through the same wind tunnel, obtaining test data of the to-be-corrected parameter X of the four airplane models, and obtaining the corrected parameter X through a formula. According to the aircraft wind tunnel support interference correction method, multiple types of aircraft models are designed to carry out wind tunnel tests, test data are obtained, a support interference deduction method is adopted, algebraic addition and subtraction averaging is carried out through results of two supports and two auxiliary supports, aerodynamic data are corrected, and the accuracy of the aerodynamic data is improved.

Description

technical field [0001] The application belongs to the field of aviation technology, in particular to a method for correcting aircraft wind tunnel support interference. Background technique [0002] In the process of aircraft design, it is the most commonly used aerodynamic analysis method to obtain the aerodynamic force of aircraft in different states by wind tunnel test. The wind tunnel test model is fixed in the wind tunnel through the support system, so the test results will definitely introduce support interference. Choosing an appropriate support interference deduction method is the key to accurately obtain aerodynamic data. [0003] At present, there are two types of support systems commonly used in wind tunnel tests: the belly support and the tail support. But for high-stealth aircraft, the rear body is flat, and the tail support will destroy the rear body surface, introducing rear body shape distortion and tail support interference, and the amount of interference i...

Claims

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Application Information

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IPC IPC(8): G01M9/04B64F5/60
CPCG01M9/04B64F5/60
Inventor 张沛良刘锦通郭旺柳王永恩张来石钧之何光洪
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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