| 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],54(11):119-129 |
| Effect of Surface Roughness on the Aerodynamic Characteristics of NACA2412 Airfoil |
| Received:May 22, 2025 Revised:June 07, 2025 |
| View Full Text View/Add Comment Download reader |
| DOI：10.16490/j.cnki.issn.1001-3660.2025.11.010 |
| KeyWord:airfoil surface roughness numerical simulation aerodynamic characteristics flow characteristics |
| Author | Institution |
| WANG Fei |
School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing , China;Southwest Institute of Technology and Engineering, Chongqing , China |
| ZHANG Kangkang |
Southwest Institute of Technology and Engineering, Chongqing , China |
| HE Duanyang |
Southwest Institute of Technology and Engineering, Chongqing , China |
| QI Ji |
China South Industries Group Corporation, Beijing , China |
| MING Xiaotian |
Southwest Institute of Technology and Engineering, Chongqing , China |
| ZHANG Jie |
Southwest Institute of Technology and Engineering, Chongqing , China |
| XIAO Peng |
Southwest Institute of Technology and Engineering, Chongqing , China |
|
| Hits: |
| Download times: |
| Abstract: |
| 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. |
| Close |
|
|
|