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Method for simulating large-proportion scaling of ultrasonic wind tunnel experiment of grid fin

A technology of wind tunnel test and scaled simulation, applied in the field of wind tunnel test

Active Publication Date: 2015-04-22
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0009] The technical problem to be solved by the present invention is to provide a large-scale scaling simulation method for grid wing supersonic wind tunnel tests, which solves the processing and strength problems encountered in large-scale scaling in wind tunnel tests, and at the same time can accurately simulate grid wings. Aerodynamic properties of the grid wing

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  • Method for simulating large-proportion scaling of ultrasonic wind tunnel experiment of grid fin
  • Method for simulating large-proportion scaling of ultrasonic wind tunnel experiment of grid fin
  • Method for simulating large-proportion scaling of ultrasonic wind tunnel experiment of grid fin

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Embodiment

[0023] As shown in Figure 1, the shape prototype of a grid wing after a large scale reduction (for example, 20 times reduction), the grid is arranged in 16×16, the grid spacing is 1.3mm, the chord length is 2.75mm, and the grid rib The thickness of plate 1 is 0.1 mm, so the shape is difficult to process in technology, and its structural strength is difficult to meet the test requirements; Fig. 2 is the equivalent model shape after adopting the method of the present invention, and its grid is reduced to 4 * 4 arrangement , the grid spacing is 5.2mm, which is the four parts of the prototype in Figure 1; in order to ensure that the axial force of the grid wing remains unchanged, the thickness of the grid rib is increased to 0.4mm, which is four times that of the prototype. The normal force of the grid wing remains unchanged, and the chord length of the grid wing is increased to 11mm, which is also four times that of the prototype. The equivalent model can be easily realized in tec...

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Abstract

The invention discloses a method for simulating a large-proportion scaling of an ultrasonic wind tunnel experiment of a grid fin. The method comprises the following steps of: after the grid fin is scaled in large proportion, carrying out the following treatment to the appearance to obtain an equivalent model appearance: reducing the number of grids according to a second proportion, and increasing chord length of the grid fin and thickness of a rib plate of the grid fin according to the second proportion; and keeping height and the thickness of the grid fin unchanged. The method for simulating the large-proportion scaling of the ultrasonic wind tunnel experiment of the grid film solves problems of processing and strength of large-proportion scaling during the wind tunnel experiment; and meanwhile, aerodynamic characteristics of the grid fin can be accurately simulated.

Description

technical field [0001] The invention belongs to the field of wind tunnel tests, in particular to a large scale reduction simulation method for grid wing supersonic wind tunnel tests. Background technique [0002] The grid wing is a space multi-lift surface system formed by numerous thin grid walls embedded in the frame. It has better lift performance in a given space, and has the advantages of compact structure and foldable structure, so it is used more and more in aircraft. [0003] In the early 1950s, the Soviet Union carried out theoretical and experimental research work on the grid wing, and at the same time carried out research on the structure, strength, and production process of the grid wing, forming a set of design methods. In the early 1990s, the United States fully evaluated the application characteristics of the grid fin on missiles, and did a lot of work on the numerical calculation of the grid fin aerodynamics, and carried out experimental verification work in...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/08
Inventor 秦永明魏忠武付增良张江
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS