自由液面对NACA0012翼型流体动力特性影响研究

刘钊; 黄闯; 杨昊; 贺旭; 党建军

doi:10.11993/j.issn.2096-3920.202205010

自由液面对NACA0012翼型流体动力特性影响研究

doi: 10.11993/j.issn.2096-3920.202205010

西北工业大学航海学院, 陕西西安, 710072

基金项目: 国家自然科学基金项目资助(51909218); 水下信息与控制重点实验室开放研究项目资助(2021JCJQLB03007); 中央高校基本科研业务费专项资金资助(D5000220168)

详细信息

通讯作者:
黄　闯(1989-), 男, 博士, 副研究员, 主要研究方向为水下超高速航行技术

中图分类号: U661.1; TJ630.2
计量
- 文章访问数: 110
- HTML全文浏览量: 21
- PDF下载量: 27
- 被引次数: 0
出版历程
- 收稿日期: 2022-05-26
- 修回日期: 2022-06-26
- 录用日期: 2023-05-23
- 网络出版日期: 2023-05-26

Free Surface Effects on the Hydrodynamic Characteristics of NACA0012

School of Marine Science and Technology, Northwestern Polytechnical University, Xi’an 710072, China

摘要

摘要: 跨介质航行器在跨越水空介质运动时, 自由液面对航行器机翼有较大的影响, 为总体设计和航行控制带来挑战。为了探究机翼从空中和水下远场接近自由液面过程的流体动力特性变化, 以NACA0012翼型为例, 采用计算流体动力学方法, 基于流体体积多相流模型建立机翼从空中和水下接近自由液面的流场数值仿真模型, 验证了模型的可行性, 研究了机翼工作在自由液面附近时的流体动力特性。结果表明: 机翼以正攻角从空中远场接近自由液面的过程中, 阻力系数逐渐减小, 升力系数和升阻比都逐渐增大; 机翼从水下远场接近自由液面的过程中, 升力系数和升阻比均逐渐减小, 当距离超过10倍弦长时, 阻力系数因兴波作用逐渐增大, 当距离小于10倍弦长时阻力系数则迅速减小。研究结果可为跨介质航行器的总体设计和航行控制提供参考。
- 跨介质航行器 /
- 自由液面 /
- 流体动力特性 /
- 机翼
Abstract: When a transmedia vehicle moves across water and air media, the free surface has a great influence on its airfoil, which brings challenges to the overall design and navigation control. To investigate the hydrodynamic characteristics of an airfoil approaching the free surface from the far field in the air and water, numerical simulation models of this process were established for a NACA0012 based on a volume of fluid multiphase flow model using computational fluid dynamics. The feasibility of the models was verified, and the hydrodynamic characteristics of the airfoil working near the free surface were studied. The results showed that the drag coefficient decreased gradually while the lift coefficient and lift-to-drag ratio increased as the airfoil approached the free surface from the far field in the air at a positive angle of attack. The lift coefficient and lift-to-drag ratio both decreased gradually when the airfoil approached the free surface from the underwater far field. When the distance was more than 10 times chord length, the drag coefficient increased gradually because of wave-induced action, and the drag coefficient decreased rapidly when the distance was less than 10 times chord length. These results can provide reference for the overall design and navigation control of transmedia vehicles.
- transmedia vehicle /
- free surface /
- hydrodynamic characteristics /
- airfoil

HTML全文

图 1 计算域边界示意图

Figure 1. Schematic of computational boundary

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图 2 网格划分细节

Figure 2. Details of grid distribution

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图 3 网格无关性验证对比图

Figure 3. Result of grid independent verification

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图 4 计算域无关性验证对比图

Figure 4. Result of computational field independent verification

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图 5 流体动力系数仿真与实验结果对比

Figure 5. Comparison of hydrodynamic coefficient between simulation and experiment

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图 6 机翼在空中工况的流体动力特性曲线

Figure 6. Hydrodynamic characteristics curves of airfoil under air condition

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图 7 机翼在水下工况的流体动力特性曲线

Figure 7. Hydrodynamic characteristics curves of airfoil under water condition

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图 8 不同工作高度的阻力系数压差分量和摩擦分量对比曲线

Figure 8. Comparison of pressure and fractional components of drag cofficients in different operational altitudes

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图 9 机翼表面压力系数变化规律

Figure 9. Surface pressure coefficient verification law of airfoil

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图 10 不同工作高度的机翼表面压力系数对比曲线

Figure 10. Comparison of surface pressure coefficient of airfoil in different operational altitudes

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图 11 不同工作深度的阻力系数压差分量和摩擦分量对比曲线

Figure 11. Comparison of pressure and fractional components of drag cofficients in different operational depths

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图 12 不同工作深度的机翼表面压力系数对比曲线

Figure 12. Comparison of surface pressure coefficient of airfoil in different operational depth

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图 13 翼型附近静压分布对比

Figure 13. Comparison of static pressure distribution around airfoil

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