TY - GEN
T1 - Flow Characteristics Around a NACA 4412 Airfoil in the Ground Proximity
AU - Sutardi, Sutardi
AU - Fuad, Mohammad Nuril
N1 - Publisher Copyright:
© 2023 American Institute of Physics Inc.. All rights reserved.
PY - 2023/6/2
Y1 - 2023/6/2
N2 - The flow characteristics around an airfoil is significantly affected by the presence of objects in the proximity of the airfoil. The main purpose of the airfoil design is to generate lift force, so that the aerodynamic performance of an airfoil can be generally expressed by the lift-to-drag ratio (CL/CD) or L/D of the respected airfoil. A good airfoil has a high value of CL/CD. A numerical study was performed to evaluate the aerodynamic characteristics of the airfoil NACA 4412 in the presence of the ground effect. A steady and incompressible flow, three-dimensional simulation are used in this study. An Ansys Fluent commercial software along with the Gambit 2.4.6 are used to obtain the simulation data. The airfoil model chord length and span are 1m and 3m, respectively. The fluid density (ρ) and fluid viscosity (μ) were to be set at 1.225 kg/m3 and 1.789 x 10-5 N.s/m2, respectively. The flow Reynlods number (Re), based on the freestream velocity and airfoil chord length, is 3 x 105. Four airfoil angles of attack (α) are used, i.e. 0, 4, 8, and 12 degrees, while the ground proximity ratios (h/c) are to be set as 0.1, 0.2, 0.4, 0.6, and 1.0. The aerodynamic characteristics that are evaluated in present study include pressure distribution, pressure and velocity contours, turbulence intensity, velocity streamline structures, and lift to drag ratio as functions of angle of attack and ground proximity ratio. The flow turbulence intensity is represented by the modified turbulence viscosity ratio of the flow. The results of this study show that the largest lift to drag ratio (CL/CD) is obtained for α = 4 deg at ground proximity (h/c) = 0.1. At this condition, the increase in CL/CD is approximately 30 percent higher than that of the airfoil without ground proximity effect. Further, the smallest CL/CD is obtained at h/c = 0.1 for α = 0 deg where CL/CD at this condition is approximately 31 percent lower than that of airfoil without ground proximity effect.
AB - The flow characteristics around an airfoil is significantly affected by the presence of objects in the proximity of the airfoil. The main purpose of the airfoil design is to generate lift force, so that the aerodynamic performance of an airfoil can be generally expressed by the lift-to-drag ratio (CL/CD) or L/D of the respected airfoil. A good airfoil has a high value of CL/CD. A numerical study was performed to evaluate the aerodynamic characteristics of the airfoil NACA 4412 in the presence of the ground effect. A steady and incompressible flow, three-dimensional simulation are used in this study. An Ansys Fluent commercial software along with the Gambit 2.4.6 are used to obtain the simulation data. The airfoil model chord length and span are 1m and 3m, respectively. The fluid density (ρ) and fluid viscosity (μ) were to be set at 1.225 kg/m3 and 1.789 x 10-5 N.s/m2, respectively. The flow Reynlods number (Re), based on the freestream velocity and airfoil chord length, is 3 x 105. Four airfoil angles of attack (α) are used, i.e. 0, 4, 8, and 12 degrees, while the ground proximity ratios (h/c) are to be set as 0.1, 0.2, 0.4, 0.6, and 1.0. The aerodynamic characteristics that are evaluated in present study include pressure distribution, pressure and velocity contours, turbulence intensity, velocity streamline structures, and lift to drag ratio as functions of angle of attack and ground proximity ratio. The flow turbulence intensity is represented by the modified turbulence viscosity ratio of the flow. The results of this study show that the largest lift to drag ratio (CL/CD) is obtained for α = 4 deg at ground proximity (h/c) = 0.1. At this condition, the increase in CL/CD is approximately 30 percent higher than that of the airfoil without ground proximity effect. Further, the smallest CL/CD is obtained at h/c = 0.1 for α = 0 deg where CL/CD at this condition is approximately 31 percent lower than that of airfoil without ground proximity effect.
UR - http://www.scopus.com/inward/record.url?scp=85163219123&partnerID=8YFLogxK
U2 - 10.1063/5.0143415
DO - 10.1063/5.0143415
M3 - Conference contribution
AN - SCOPUS:85163219123
T3 - AIP Conference Proceedings
BT - Proceedings of the 7th International Conference of Science, Technology, and Interdisciplinary Research, IC-STAR 2021
A2 - Susanto, Misfa
A2 - Nor, Fethma M.
A2 - Nasution, Ahmad Kafrawi
PB - American Institute of Physics Inc.
T2 - 7th International Conference of Science, Technology, and Interdisciplinary Research, IC-STAR 2021
Y2 - 26 October 2021 through 27 October 2021
ER -