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Numerical modeling on dynamics of droplet in aircraft wing structure at different velocities
Aircraft Engineering and Aerospace Technology ( IF 1.5 ) Pub Date : 2021-10-13 , DOI: 10.1108/aeat-04-2021-0115
Nithya Subramani 1 , Sangeetha M. 2 , Vijayaraja Kengaiah 3 , Sai Prakash 4
Affiliation  

Purpose

The purpose of this paper is to find the droplets impact on the airplane wing structure. Two kinds of characteristics of the droplet at different velocity and viscosity are assumed. The droplet is assumed to be spherical cubic form and it is injected from the convergent divergent nozzle with a passive control.

Design/methodology/approach

This paper presents the results of a numerical simulation of droplet impact on the horizontal surface. The effects of impact parameters are studied. The splash effect of the droplet also visualized. The results are presented in form of stress, strain, displacement magnitude of the droplet.

Findings

Crosswire is used as passive control. The behavior of the droplet impact is observed based on the kinetic energy and the gravitational forces.

Originality/value

The results predict that smooth particle hydrodynamic designed droplet not only depend on the equation of state of the droplet but also the injection velocity from the nozzle. It also determined that droplet velocity is depending on the viscosity of the fluid.



中文翻译:

不同速度下飞机机翼结构液滴动力学数值模拟

目的

本文的目的是找出液滴对飞机机翼结构的影响。假设液滴在不同速度和粘度下的两种特性。液滴被假定为球形立方形式,并从带有被动控制的会聚扩张喷嘴喷射。

设计/方法/方法

本文介绍了液滴撞击水平表面的数值模拟结果。研究了冲击参数的影响。水滴的飞溅效果也可视化了。结果以液滴的应力、应变、位移大小的形式呈现。

发现

Crosswire 用作被动控制。基于动能和重力观察液滴撞击的行为。

原创性/价值

结果预测,光滑粒子流体动力学设计的液滴不仅取决于液滴的状态方程,还取决于喷嘴的喷射速度。它还确定液滴速度取决于流体的粘度。

更新日期:2021-10-13
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