Icing wind tunnel test similarity conversion method based on numerical simulation

A conversion method and wind tunnel test technology, applied in the field of numerical simulation, can solve the problems of uneven cloud field, increase in speed, decrease in MVD, etc., to achieve the effect of improving convenience and usability, and reducing performance requirements

Active Publication Date: 2020-08-21
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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Problems solved by technology

However, using the Ruff method has many limitations, and using WeL as the basis for speed selection will inevitably lead to an increase in the converted speed: the higher the speed, the more uneven the cloud and fog field in the icing wind tunnel; at the same time, the MVD will decrease, even exceeding the capacity of the icing wind tunnel scope

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  • Icing wind tunnel test similarity conversion method based on numerical simulation
  • Icing wind tunnel test similarity conversion method based on numerical simulation
  • Icing wind tunnel test similarity conversion method based on numerical simulation

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[0035] In order to make the purpose, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described below in conjunction with the drawings in the embodiments of the present application.

[0036] In the subscripts of the parameters listed below, s is the experimental condition of model icing, and r is the reference icing condition of the full-scale object.

[0037] Taking a certain wing with a chord length of 3.8m as an example, due to the size limitation, the wing icing test needs to be carried out with a scale model, and the model scale is 1:2. The reference conditions are shown in Table 1.

[0038] Table 1 Reference state test

[0039] Test parameters T st,S (℃)

MVD(μm) LWC(g / m³) H(m) V(m / s) chord(m) Time (Sec) reference status -7 30 0.268 3000 110 3.8 1350

[0040] For the above states, the similar transformation method b...

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Abstract

The invention discloses an icing wind tunnel test similarity conversion method based on numerical simulation, and the method comprises the steps: calculating parameters needed by a test through a similarity criterion, and adjusting the parameters if the parameters exceed an icing wind tunnel capability envelope range, so as to enable the parameters to meet the icing wind tunnel capability enveloperange; the states before and after conversion being subjected to analog calculation through CFD software, and comparing ice type calculation results before and after conversion to evaluate whether the conversion results meet requirements or not; and if the calculation result comparison shows that the ice type difference before and after conversion is large, parameters should be reselected. According to the method, accurate simulation and experiment results can be obtained in the range of the existing icing wind tunnel capability envelope, and the performance requirement on the icing wind tunnel is reduced.

Description

technical field [0001] The present application relates to the field of numerical simulation, in particular, to a numerical simulation of icing wind tunnel experiments. Background technique [0002] The icing wind tunnel test is an important means to evaluate the safety performance of the aircraft. Through the test method, the influence of the icing on the flight performance of the aircraft can be obtained, or the performance of the anti-icing system of the aircraft can be assessed. For larger aircraft or component models, the major icing wind tunnels in the world cannot conduct full-scale tests at present, so the models need to be scaled down. In order to obtain an ice shape that is geometrically similar to the original size in the icing wind tunnel test of the scale model, it is necessary to perform a similar transformation on the test conditions. The similarity conversion method is an analysis method implemented on the scaled model. It calculates the test state parameters...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/28G06F111/10G06F113/08G06F119/14G06F119/08
Inventor 刘宇易贤王强李维浩任靖豪
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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