Abstract
This report is using the finite element analysis method to investigate the performance of an airfoil (NACA 0100-35), which uses 2D computational fluid dynamics simulations based on ANSYS to find the lift and drag coefficients under different conditions. The boundary conditions are defined as follows: The density is 1kg/m3, gauge pressure is 0, and airflow velocity is 50m/s. Also the Reynolds number is considered during the simulation. As a result, the simulation shows the stalling points and efficiencies of the airfoil under different angles of attack. The simulation also plots the contours and stream lines in these conditions.
Reference8 articles.
1. Benson T. National Aeronatics and Space Administration. Aerodynamic Forces, retrieved from http://www.grc.nasa.gov/WWW/k-12/airplane/presar.html (n.d.)
2. Cited from Wikipedia: http://en.wikipedia.org/wiki/Lift_coefficient
3. CFD Analysis of an Aerofoil
4. Benson T. National Aeronatics and Space Administration. Aerodynamic Forces, retrieved from http://www.grc.nasa.gov/WWW/k-12/airplane/liftco.html (n.d.)
5. Computational Fluid Dynamics Analysis of Wind Turbine Blade at Various Angles of Attack and Different Reynolds Number
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