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A parameterization method of ice shape for wind tunnel test

A wind tunnel test and parameterization technology, applied in the aviation field, can solve problems such as difficulty in describing ice shapes, and achieve the effect of high engineering application value.

Active Publication Date: 2021-10-19
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Under different icing conditions, different ice shapes will be obtained. However, most of the ice objects obtained by the icing wind tunnel test are irregular and have many burrs. Therefore, it is extremely difficult to describe the ice objects.

Method used

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  • A parameterization method of ice shape for wind tunnel test
  • A parameterization method of ice shape for wind tunnel test
  • A parameterization method of ice shape for wind tunnel test

Examples

Experimental program
Comparison scheme
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Embodiment 1

[0039] The ice shape parameterization method for wind tunnel test in this embodiment includes the following steps:

[0040] S1. Determine the ice shape characteristic points; carry out the wing icing wind tunnel test in the icing wind tunnel, obtain the airfoil icing ice pattern, convert the solid icing ice pattern into the ice shape curve in the Cartesian coordinate system, and calculate the ice shape curve in the ice shape curve OK as above figure 1 Feature points shown: lower limit point a, lower ice angle point b, stagnation point c, upper ice angle point d, upper limit point e, and lower ice angle point b projected on the airfoil point b', stagnation point c Project point c' on the airfoil and point d on the ice angle; project point d' on the airfoil;

[0041] S2. Obtain ice shape quantization parameters; quantify the feature points of step S1, and obtain such figure 2 The following seven ice shape quantification parameters are shown: the height of the upper ice angle ...

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Abstract

The invention discloses an ice shape parameterization method used in wind tunnel tests. The ice shape parameterization method firstly determines the ice shape feature points; secondly obtains the ice shape quantization parameters; thirdly performs the coordinate conversion of the local coordinate system of the feature points; finally performs the ice shape parameterization based on the local coordinate system. The ice shape parameterization method is a segmented ice shape parameterization method. By determining the ice shape feature points, using relevant quantitative parameters to establish a local coordinate system, and using segmented fitting to obtain a parameterized ice shape curve, the aircraft can be The icing wind tunnel test results are simplified to provide technical support for the research on the influence of airfoil aerodynamic characteristics, which has high engineering application value.

Description

technical field [0001] The invention belongs to the technical field of aviation, and in particular relates to an ice shape parameterization method for wind tunnel tests. Background technique [0002] When the aircraft encounters clouds or supercooled raindrops containing supercooled water droplets during flight, the supercooled water droplets will freeze on the airframe to form icing phenomenon. Aircraft icing seriously affects the safe flight of aircraft and may lead to safety accidents. Therefore, research on aircraft icing has received extensive attention. [0003] At this stage, the icing wind tunnel test is one of the important means to study aircraft icing, and the ice shape is the main result obtained from the icing wind tunnel test. The influence of icing on the aerodynamic characteristics of the aircraft can be studied through the ice shape. Under different icing conditions, different ice shapes will be obtained. However, most of the ice objects obtained by icing w...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 钱炜祺张显才何磊周宇邵元培
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT