结冰风洞中液滴过冷特性数值研究

doi:10.7527/S1000-6893.2017.121254

Abstract

Abstract:

In order to understand the supercooling of the droplet in the icing wing tunnel,a numerical method based on Eulerian theory is developed to simulate the gas-droplet flow in an icing wind tunnel.Using the numerical method,a parametric study is firstly conducted,then the influence of 3D contraction of a typical icing wind tunnel configuration is investigated,and finally the supercooling of the droplet in the test section of the wind tunnel is evaluated.The results show that the droplet diameter and gas velocity have a great effect on the supercooling of the droplet.The larger the droplet diameter or airspeed,the larger distance where the droplet temperature is close to the gas temperature.The process of droplet heat transfer in a typical icing wind tunnel configuration can be divided into two stages:the quasi-1D stage and the 3D contraction stage.The influence of the 3D contraction stage on the droplet supercooling is greater than that of the quasi-1D stage.Therefore,the 3D contraction of the typical icing wind tunnel configuration has a significant effect on the supercooling of the droplet.In typical test conditions,the small droplets with the diameter smaller than 40 μm are supercooling (the temperature difference between droplet and gas is lower than 2 ℃) in the test section,but big droplets with the diameter bigger than 100 μm cannot be supercooling (the temperature difference between the droplet and gas is higher than 5 ℃) at the high test section velocity (the airspeed is 157 m/s).

Key words: aircraft icing, icing wind tunnel, droplet, supercooling, numerical simulation

CLC Number:

V221.3

GUO Xiangdong, WANG Zixu, LI Ming, XIAO Chunhua. Numerical study of supercooling characteristics of droplet in icing wind tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(10): 121254-121254.

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Numerical study of supercooling characteristics of droplet in icing wind tunnel

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