The thickness of the air foil is approximately estimated as 0.14 m. Total length of the air foil is selected as 1 m. Grid shape selected as a square and grid spacing size is 0.01 m. Chamber line is the locus of points midway between the upper and lower surface of an airfoil. The straight line joining the leading edge and trailing edge of airfoil section is chord line. The trailing edge is the point of minimum curvature at the rear of the airfoil. The calculations has been performed for different angle of attacks starting from to by increasing the angle for each trial.Īs it can be seen in the Fig.1, the point at front of the airfoil is a leading edge. The kinematic viscosity is calculated as 3.89x10e-5 m 2 s −1.
The dynamic viscosity is µ = 4.58×kg/m.s and the density at the given temperature is ρ = 1.177 kg/m3. For this Mach number, the flow is assumed as compressible. The total temperature of the free stream is estimated at 300 K, which is the same as the ambient temperature. Velocity of the flow is selected as 50 m/s.
The Mach number is determined as M = 0.1457. Wortmann FX 75-141 air foil profile is used for the CFD analysis in this project. In this project, the flow pattern of the Wortmann FX 75-141 air foil has been analysed on two-dimensional turbulent flow and computational fluid dynamic analysis has been implemented on the air foil to find lift and drag coefficient values at different angles of attacks by using Siemens Star CCM+ 12.
Therefore, it is of interest to establish a validation regime of computational methods for design and analytical purposes by comparing the results. Of primary importance are the airfoil parameters. In order to keep costs low, computational methods are more commonly used, rather than wind tunnel and flight tests, to predict the performance and handling characteristics of aircraft.
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