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飞机结冰表面上的液态水受气流吹拂作用会发生向后溢流,从而影响结冰区域范围及防冰系统设计;为了获得水膜流动规律,对水平平板表面上气流剪切驱动的水膜流动进行了实验测量和建模分析。通过水膜流动风洞试验台产生高速气流驱动水膜的流动,使用色散共焦位移计测量同一位置的水膜在不同时刻的厚度变化,结果表明气-液界面由底层薄水膜和多种尺度的波动组成,具有变化速度快随机性强的特点。通过水膜厚度随气流速度及水膜雷诺数的变化规律,发现平均水膜厚度与两者均呈现出单调非线性的依赖关系。基于薄水膜流动理论和平均水膜厚度实验结果,提出了高速气流剪切作用下的气-液波动界面剪切因子计算式,适用于风速17.8~52.2m/s,水膜雷诺数26~128之间的平板水膜流动计算。
The liquid water on the icing surface of the airplane will be backflowed by the airflow blowing, which will affect the icing area and the anti icing system design. In order to obtain the law of water flow, the water film Flows were measured experimentally and modeled. The flow of water film driven by high-speed airflow was produced by the flow-field test bed of water film. The thickness change of the water film at the same location at different time was measured by the dispersion confocal displacement meter. The results showed that the gas- The composition of the fluctuations of the scale, with the rapid changes in the characteristics of strong randomness. Through the variation of water film thickness with the air velocity and the Reynolds number of the water film, it is found that the average water film thickness exhibits a monotonic non-linear dependence on both. Based on the experimental results of thin water film flow and average water film thickness, the calculation formula of the shear factor of gas-liquid interface under high velocity airflow shear is proposed, which is suitable for wind speed 17.8 ~ 52.2m / s, water film Reynolds number 26 ~ 128 between the flat water film flow calculation.