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A method and system for quantitative evaluation of ice shape and ice angle in icing wind tunnel test

A technology of quantitative evaluation and wind tunnel test, applied in the aviation field, to achieve the effect of improving calculation accuracy and efficiency

Active Publication Date: 2020-09-29
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Application Information

AI Technical Summary

Problems solved by technology

[0007] In order to solve the problem of quantitative evaluation of ice shape area in icing wind tunnel test, the present invention provides a method and system for quantitative evaluation of ice shape and ice angle in icing wind tunnel test, which is used to calculate discretized ice shape and airfoil digital points. It does not involve complex mathematical formulas and numerical iterative processes, and can quickly and efficiently complete the quantitative calculation of ice shape characteristic parameters, which is suitable for large-scale experimental ice shape and ice angle quantitative evaluation tasks

Method used

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  • A method and system for quantitative evaluation of ice shape and ice angle in icing wind tunnel test
  • A method and system for quantitative evaluation of ice shape and ice angle in icing wind tunnel test
  • A method and system for quantitative evaluation of ice shape and ice angle in icing wind tunnel test

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Effect test

Embodiment 1

[0073] A method for quantitative evaluation of ice shape and ice angle in icing wind tunnel tests, such as figure 1 shown, including the following steps:

[0074] (1) Digitized ice geometric contour lines

[0075] Digitally scan the grid drawing of the ice contour drawn in the test, define the digital coordinate system, extract the discrete coordinate points of the airfoil and the ice contour, and draw the ice contour map;

[0076] specifically,

[0077] 1-1. Use a large-format scanner to scan the grid drawing of the ice contour line, and output the digital ice contour line picture as figure 2 shown;

[0078] 1-2. Define the digital coordinate system, such as image 3 As shown, the leading edge point of the airfoil is set as the coordinate origin, the X-axis points to the tail of the airfoil along the chord line of the airfoil, and the Y-axis points from the lower airfoil (pressure surface) of the airfoil to the upper airfoil (suction surface);

[0079] 1-3. Use picture ...

Embodiment 2

[0128] Adopt a kind of icing wind tunnel test ice angle quantitative evaluation method of the present invention, calculate the ice angle characteristic parameter of flow direction ice shape, such as Figure 10 As shown, the ice corner thickness T s and angle θ s are 0.033 and 199°, respectively.

Embodiment 3

[0130] Adopt a kind of icing wind tunnel test ice angle quantitative evaluation method of the present invention, calculate the ice angle characteristic parameter of horn-like ice shape, such as Figure 11 As shown, the middle and upper ice angle thickness T du and angle θ du are 0.11 and 147° respectively, the lower ice angle thickness T dl and angle θ dl are 0.102 and 236°, respectively.

[0131] The results show that the present invention can accurately extract and calculate typical ice angle characteristic parameters, can effectively solve the problem of quantitative evaluation of ice angle in icing wind tunnel tests, and provide critical ice shape selection, anti-icing system performance evaluation, ice Provide technical support for test objectives such as model development.

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Abstract

The present invention is applicable to the field of aviation, and provides a method and system for quantitatively evaluating the ice shape and ice angle in icing wind tunnel tests. Firstly, for the ice shape contour obtained in the icing wind tunnel test, the ice shape geometric contour line digitization method is adopted, The discrete coordinate points of the ice contour line are obtained, and then for the discrete points of the ice shape, the ice shape type judgment criterion is established to judge the ice shape type, and the corresponding ice shape characteristic parameters are calculated according to different ice shape types. The evaluation method and system of the present invention are suitable for large-scale experimental ice shape and ice angle quantitative evaluation tasks. The calculation method does not involve complicated mathematical formulas and time-consuming numerical iteration processes, and can quickly and efficiently complete the ice shape and ice angle quantitative evaluation.

Description

technical field [0001] The invention belongs to the field of aviation, and in particular relates to a method and system for quantitatively evaluating the ice shape and ice angle in an icing wind tunnel test. Background technique [0002] When an aircraft flies in the clouds, supercooled water droplets (that is, liquid water droplets whose temperature is below freezing point) in the clouds will continuously hit the windward side of the aircraft, causing the surface to freeze. Aircraft icing widely exists in flight practice and seriously threatens flight safety. The icing wind tunnel is an important ground test equipment for aircraft icing research and aircraft component anti-icing system verification, and it plays an important role in aircraft icing airworthiness certification. In the icing wind tunnel test, the geometric profile of the ice accretion shape is the most important icing test result, and it is the key parameter for the selection of critical ice shape, performanc...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/20G06F111/10
CPCG06F30/15G06F30/20G06F2111/10
Inventor 郭向东赵献礼陈圆圆白云卯
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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