王飞,张康康,何端阳,齐迹,明晓添,张杰,肖朋.NACA2412翼型表面粗糙度对气动特性影响研究[J].表面技术,2025,54(11):119-129.
WANG Fei,ZHANG Kangkang,HE Duanyang,QI Ji,MING Xiaotian,ZHANG Jie,XIAO Peng.Effect of Surface Roughness on the Aerodynamic Characteristics of NACA2412 Airfoil[J].Surface Technology,2025,54(11):119-129 |
| NACA2412翼型表面粗糙度对气动特性影响研究 |
| Effect of Surface Roughness on the Aerodynamic Characteristics of NACA2412 Airfoil |
| 投稿时间：2025-05-22 修订日期：2025-06-07 |
| DOI：10.16490/j.cnki.issn.1001-3660.2025.11.010 |
| 中文关键词: 翼型 表面粗糙度 数值模拟 气动特性 流动特性 |
| 英文关键词:airfoil surface roughness numerical simulation aerodynamic characteristics flow characteristics |
| 基金项目: |
| 作者 | 单位 |
| 王飞 | 南京理工大学 机械工程学院，南京 210094;西南技术工程研究所，重庆 400039 |
| 张康康 | 西南技术工程研究所，重庆 400039 |
| 何端阳 | 西南技术工程研究所，重庆 400039 |
| 齐迹 | 中国兵器装备集团有限公司，北京 100089 |
| 明晓添 | 西南技术工程研究所，重庆 400039 |
| 张杰 | 西南技术工程研究所，重庆 400039 |
| 肖朋 | 西南技术工程研究所，重庆 400039 |
|
| Author | Institution |
| WANG Fei | School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China;Southwest Institute of Technology and Engineering, Chongqing 400039, China |
| ZHANG Kangkang | Southwest Institute of Technology and Engineering, Chongqing 400039, China |
| HE Duanyang | Southwest Institute of Technology and Engineering, Chongqing 400039, China |
| QI Ji | China South Industries Group Corporation, Beijing 100089, China |
| MING Xiaotian | Southwest Institute of Technology and Engineering, Chongqing 400039, China |
| ZHANG Jie | Southwest Institute of Technology and Engineering, Chongqing 400039, China |
| XIAO Peng | Southwest Institute of Technology and Engineering, Chongqing 400039, China |
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| 中文摘要: |
| 目的 为获取宽飞行工况下表面粗糙度对翼型气动特性和流场特性的影响，指导翼型设计和开发，对翼型不同表面粗糙度开展数值仿真研究。方法 利用CFD数值模拟方法，采用SST k-ω湍流模型，以NACA2412翼型为研究对象，开展了不同表面粗糙度下翼型的气动特性数值模拟与分析，得到了不同表面粗糙度下翼型摩擦阻力系数、总阻力系数、升力系数等变化规律以及各工况下的翼型流场分布。结果 当翼型表面粗糙度小于敏感粗糙度kcr时，翼型表面摩擦阻力系数急剧增大，升力系数急剧减小，当翼型表面粗糙度大于kcr值时，翼型气动特性对粗糙度不敏感。Ma=0.2时，翼型表面敏感粗糙度kcr为0.25 mm，随着粗糙度的增加，翼型的临界攻角逐渐减小;敏感粗糙度下，临界攻角为13°，较光滑翼型减小了3°，其升力系数在各攻角下较光滑表面降低8.7%~31.2%。随着马赫数增大，翼型表面敏感粗糙度kcr减小，临界攻角减小。Ma=0.6时，翼型表面敏感粗糙度kcr为0.15 mm，临界攻角随粗糙度变化不大，各粗糙度下翼型临界攻角已减小至8°;敏感粗糙度下，8°攻角及以下，升力系数较光滑表面降低8.3%~11.8%，超过8°攻角后，由于粗糙翼型和光滑翼型均达到临界攻角，翼型升力系数受粗糙度影响较小。结论 随着翼型表面粗糙度的增加，翼型摩擦阻力系数和总阻力系数增大，但随着攻角和马赫数增大，摩擦阻力占翼型总阻力比例逐渐减小，翼型总阻力增长不大;随着翼型表面粗糙度的增加，翼型升力系数减小，翼型边界层厚度增大，翼型表面发生流动分离、产生失速现象的临界攻角减小。研究内容对不同飞行速度下飞行器翼型表面粗糙度等翼型设计和开发具有一定的指导意义。 |
| 英文摘要: |
| In order to investigate the effect of surface roughness on the aerodynamic and flow characteristics of the NACA2412 airfoil under wide flight conditions and guide the design of airfoils, the work aims to take the airfoil as the research object and adopt CFD numerical simulation method and two-dimensional N-S equation as well as SST k-ω turbulence model to carry out numerical simulation and analysis of the aerodynamic characteristics of the airfoil under different surface roughness conditions at different Mach numbers and angles of attack. The variation laws of the frictional drag coefficient, total drag coefficient, lift coefficient and flow field distribution of the airfoil under different surface roughness conditions were obtained. The results showed that when the surface roughness of the airfoil was less than the sensitive roughness kcr, the frictional drag coefficient of the airfoil surface increased sharply and the lift coefficient decreased sharply. When the surface roughness of the airfoil was greater than the kcr value, the aerodynamic characteristics of the airfoil were insensitive to roughness. When Ma=0.2, the sensitive roughness kcr of the airfoil surface was 0.25 mm. As the roughness increased, the critical angle of attack of the airfoil gradually decreased. Under sensitive roughness, the critical angle of attack was 13°, which was 3° lower than that of a smoother airfoil. Its lift coefficient was reduced by 8.7% to 31.2% compared to a smoother surface at various angles of attack. As the Mach number increased, the surface sensitivity roughness kcr of the airfoil decreased, and the critical angle of attack decreased. When Ma=0.6, the sensitive roughness kcr of the airfoil surface was 0.15 mm, and the critical attack angle of the airfoil did not change significantly with roughness. The critical attack angle of the airfoil was reduced to 8° for each roughness value. Under sensitive roughness, the lift coefficient decreased by 8.3% to 11.8% compared to smooth surfaces at angles of attack of 8° and below. After the angle of attack exceeded 8°, both rough and smooth airfoils reached the critical angle of attack, and the lift coefficient of the airfoil did not vary significantly with roughness. The aerodynamic characteristics study of different wing surface roughness shows that as the airfoil surface roughness increases, the friction drag coefficient of the airfoil increases, and the total drag coefficient of the wing increases. However, as the angle of attack and Mach number increase, the proportion of friction drag to the total drag of the airfoil gradually decreases, and the growth of the total drag of the airfoil is not significant. As the surface roughness of the airfoil increases, the lift coefficient of the airfoil decreases, the thickness of the airfoil boundary layer increases, and the critical angle of attack for flow separation and stall phenomenon on the airfoil surface decreases. The study has certain guiding significance for the design and development of airfoils at different flight speed, such as surface roughness. In the process of airfoil design and development, while ensuring machining accuracy, it is also necessary to consider methods such as spraying modified coatings or protective coatings to reduce the erosion and burning effect of high-temperature and high-pressure gunpowder gas on the airfoil surface during launch, suppress the adhesion of ice crystals during flight, maintain the surface roughness of the airfoil at the micrometer level, and avoid a sharp increase in surface roughness of the airfoil leading to a decrease in aerodynamic performance. |
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