The table below shows the lift, drag, and moment coefficients about the quarter

Question

The table below shows the lift, drag, and moment coefficients about the quarter chord for NACA 2412 airfoil as a function of angle of attack. Add two columns to the table above showing the values of the normal and axial force coefficients as the angle of attack varies. Determine the expression for x_cp/c as a function of as a function of c_m; and c_n. Then add a column for x_cp/c in the table above. Plot on a graph paper the variation ofx_cp/c with angle of attack (alternatively, you can also plot using software like MATLAB or Excel). Comment on how the location of the center of pressure varies as the angle of attack is increased from -2.0 degree to 14 degree

Explanation / Answer

c)

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