Airfoil Analysis

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This paper aims in developing a new airfoil profile NACA 6430 for low wind density areas and comparing the results of newly developed airfoil characteristic with the existing NACA 0012H and NACA 4412 using computational fluid dynamics. The CFD analysis is carried out using ANSYS 14.0 fluent software angle of attack between 0-200. The co-efficient of lift and drag are monitored and pressure and velocity distribution for various angle of attack are plotted.

Keywords—NACA airfoil, angle of attack , co-efficient of lift, co-efficient of drag

Wind energy is one of vital source of power in the present and future. Among the conventional source of energy wind energy is one of the cheapest source of energy. Modern researches are
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Nomenclature of airfoil The geometry of the airfoil is described with a variety of terms as shown in figure 1:
• The leading edge is the point at the front of the airfoil that has maximum curvature (minimum radius).
• The trailing edge is defined similarly as the point of maximum curvature at the rear of the airfoil.
• The chord line is the straight line connecting leading and trailing edges. The chord length, or simply chord, , is the length of the chord
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Its shape depends on the thickness distribution along the chord.
• The thickness of an airfoil varies along the chord. Thickness is measured perpendicular to camber line or chord line.The suction surface (a.k.a. upper surface) is generally associated with higher velocity and lower static pressure.[6] Fig 1 nomenclature of airfoil
A. Generation of airfoil
The NACA airfoils are generated with the help of the online airfoil generator. The data of existing NACA 0012H and NACA 4412 airfoils are taken from the airfoil tool database. NACA 6430 is developed from NACA 6412 by increasing its thickness as a percentage of chords.
B. Computational flow analysis in airfoil
The airfoils are analysed for varying angle of attack from 00 to 200 with a increment of 20. The analysis is carried out in ANSYS fluent 14.0.
1. Geometry creation
The co-ordinate points for the airfoil are obtained from the database. This points are imported in ANSYS workbench 14.0. After importing the co-ordinates of airfoil the boundary for the airfoil is created as shown in the figure 2. Figure 2 Geometry creation for airfoil

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