2-D Steady State CFD analysis of Clark Y Airfoil
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An analysis of a clark y airfoil in 2D to determine the lift coefficient and drag coefficient of the airfoil. The analysis is done to better understand the characteristics of the airfoil and then compare them to its 3D counterpart.
We have a clark y airfoil moving in air with a velocity of 25 m/s and angle of attack of 4°. We have to determine the lift coefficient and drag coefficient of the airfoil and plot the pressure coefficient against percentage of chord length.
For this purpose we create a model of the clark y airfoil in 2D space and place it in a c-domain with length equal to 8 times the chord length.
We perform a steady state CFD analysis with gravity off using the SST k-omega turbulence mode land the results are published in post.
The following results are obtained from the analysis:
These results track well with empirical data on the clark y airfoil.
