Question: Two-dimensional lift-drag data for the NACA 2412 airfoil with 2 percent camber (from Ref. 12) may be curve-fitted accurately as follows: CL 0.178 + 0.109
(a) The lift-curve slope and
(b) The angle of zero lift with theory, Eq. (8.69).
(c) Prepare a polar lift-drag plot and compare with Fig. 7.25
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