If your institution has an online potential fl ow boundary element computer code
Chapter 8, Problem p8.114(choose chapter or problem)
If your institution has an online potential fl ow boundary element computer code, consider fl ow past a symmetric airfoil, as in Fig. P8.114. The basic shape of an NACA symmetric airfoil is defi ned by the function [12] 2y tmax < 1.48451/2 2 0.63 2 1.7582 1 1.42153 2 0.50754 where 5 x/C and the maximum thickness tmax occurs at 5 0.3. Use this shape as part of the lower boundary for zero angle of attack. Let the thickness be fairly large, say, tmax 5 0.12, 0.15, or 0.18. Choose a generous number of nodes ($60), and calculate and plot the velocity distribution V/U along the airfoil surface. Compare with the
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