The rate of change of moment coefficient with respect to the angle of attack, $\frac{\mathrm{d} \mathrm{C}_{\mathrm{m}}}{\mathrm{d} \alpha},$ at half chord point of a thin airfoil, as per approximations from the thin airfoil theory is

(A) $\pi / 4$ radian $^{-1}$

(B) $\pi / 2$ radian $^{-1}$

(C) $\pi$ radian $^{-1}$

(D) $2 \pi$ radian $^{-1}$

The rate of change of moment coefficient with respect to the angle of attack, $\frac{\mathrm{d} \mathrm{C}_{\mathrm{m}}}{\mathrm{d} \alpha},$ at half chord point of a thin airfoil, as per approximations from the thin airfoil theory is

(A) $\pi / 4$ radian $^{-1}$

(B) $\pi / 2$ radian $^{-1}$

(C) $\pi$ radian $^{-1}$

(D) $2 \pi$ radian $^{-1}$

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