Home / Current Issue / Paper 1706583
Aerodynamic Simulation of NACA 0012 Airfoil at Low Angles of Attack Using CFD
Subject area: Science,Engineering and Technology · Area of research: Mechanical Engineering
Abstract
The NACA four-digit classification system defines airfoil geometry through a four-part code. Maximum camber (first digit, % of chord), camber position (second digit, tenths of chord), and maximum thickness (last two digits, % of chord) are specified. Notably, a 12% maximum thickness indicates a symmetric airfoil profile with no camber. This study examines the aerodynamic performance of a NACA 0012 airfoil under subsonic flow conditions. We analyze the behavior of the airfoil in terms of the lift it produces as a result of air attacking it. We calculate lift against a C-type geometry. The mathematical model considers varying angles of attack for values of inlet velocity. The mathematical model includes the Nervier-Stokes equations and the Standard k turbulence model to capture the turbulence. The model involves solving a set of nonlinear partial equations and differential equations simultaneously. The finite volume method serves as the solver for this task. ANSYS Workbench 16.2 includes FLUENT for solving all simulations.
Keywords
NACA0012 Airfoil, Lift and Drag Coefficient, Angle of attack, Numerical Analysis, CFD, ANSYS Fluent.
References
[1] Achleitner, J..Rohde-Brandenburger, K.and Rogalla von Bieberstein, P,; Sturm, F.; Hornung M 2019 Aerodynamic Design of A Morphing Wing Sailplane AIAA Aviation Forum 2816
[2] Singh, I.,2017 Effect of Plain Flap Over the Aerodynamic Characteristics of Airfoil NACA 66- 015 International Journal of Innovative Science and Research Technology 2 353-365.
[3] Katz, J. and R, Largman, R., 1989 Effect of 90-Degree Flap on the Aerodynamics of a TwoElement Airfoil Journal of Fluids Engineering 111.
[4] Mahmood, Z, Khan., M, K, Scale., W, J, Bruun., H, H. 1995 Comparison of measurement and computed Transaction nce of Multi Gurney Flaps Configuration on Airfoil Engineering Research Journal (ERJ) 1 34-42.
[5] Bartlett D. W., Patterson Jr J. C., The NASA supercritical-wing technology. CTOL Transport Technol. Conf. (NASA-TM-78731) 1978.
[6] Hsiun, C. and Chen, C., 1996. Aerodynamic characteristics of a two-dimensional airfoil with ground effect. Journal of Aircraft, 33(2), pp.386-392.
[7] Barber, T. Leonard, E. and Archer, D., 1998. Appropriate CFD techniques for the prediction of ground effect aerodynamics. Proceedings of Workshop ‘WISE up to ekranoplan GEMs’, University of New South Wales, Sydney, Australia.
[8] Chun, H. and Chang, R., 2003. Turbulence flow simulation for wings in ground effect with two ground conditions: fixed and moving ground. International Journal of Maritime Engineering, 145, pp.51-68.
[9] Wu, C.K. and Rozhdestvensky, K.V., 2001. High-Reynoldsnumber flow computations for wings in ground effect. Proceedings of 6th International Conference on Fast Sea Transportation, Southampton, UK.
[10] Belamadi, R., Djemili, A., Ilinca, A. & Mdouki, R. Aerodynamic performance analysis of slotted airfoils for application to wind turbine blades. Journal of Wind Engineering and Industrial Aerodynamics 151, 79–99 (2016), https://doi.org/10.1016/j.jweia.2016.01.011.
[11] Beyhaghi, S. & Amano, R. S. Improvement of Aerodynamic Performance of Cambered Airfoils Using Leading-Edge Slots. Journal of Energy Resources Technology 139, (2017), https://doi.org/10.1115/1.4036047.
[12] Almusawi, M., Rishack, Q. & Al-fahham, M. Effect of Spanwise Semicircular Groove on NACA 0012 Airfoil. Basrah Journal for Engineering Sciences (BJES), 2022, 22 (2), 23–26. https://doi.org/10.33971/bjes.22.2.4.
[13] Venkatesh, D. T., Chikkanna, D. N., Basawaraj, D., Palekar, S. G. & Raikar, A. M. Design and Computational Analysis of Continuous Groove Effect on the Wing. International Research Journal of Engineering and Technology 08(10), 66, (2021), https://www.irjet.net/volume8-issue10
How to cite this paper
@article{1706583,
author = {Muhammad Rashid Iqbal, Sana Marryam},
title = {Aerodynamic Simulation of NACA 0012 Airfoil at Low Angles of Attack Using CFD},
journal = {Iconic Research And Engineering Journals},
year = {2024},
volume = {8},
number = {5},
pages = {537-542},
issn = {2456-8880},
url = {https://www.irejournals.com/formatedpaper/1706583.pdf},
abstract = {The NACA four-digit classification system defines airfoil geometry through a four-part code. Maximum camber (first digit, % of chord), camber position (second digit, tenths of chord), and maximum thickness (last two digits, % of chord) are specified. Notably, a 12% maximum thickness indicates a symmetric airfoil profile with no camber. This study examines the aerodynamic performance of a NACA 0012 airfoil under subsonic flow conditions. We analyze the behavior of the airfoil in terms of the lift it produces as a result of air attacking it. We calculate lift against a C-type geometry. The mathematical model considers varying angles of attack for values of inlet velocity. The mathematical model includes the Nervier-Stokes equations and the Standard k turbulence model to capture the turbulence. The model involves solving a set of nonlinear partial equations and differential equations simultaneously. The finite volume method serves as the solver for this task. ANSYS Workbench 16.2 includes FLUENT for solving all simulations.},
keywords = {NACA0012 Airfoil, Lift and Drag Coefficient, Angle of attack, Numerical Analysis, CFD, ANSYS Fluent.},
month = {November},
}