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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.
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},
}