Engineering, 12.08.2020 07:01, tessa70

For a flat plate airfoil, use thin airfoil theory to plot the distributions of chordwise vorticity (circulation per unit length) for an angle of attack of 2 and 5 de- grees. Use the trapz function in MATLAB to numerically integrate these distributions to calculate the lift coefficient at these angles of attack. How does it compare with C1=27a. Note, Ap pVo

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For a flat plate airfoil, use thin airfoil theory to plot the distributions of chordwise vorticity (...