Discussion
A symmetric airfoil is set at an angle of attack of \(5^\circ\). Using thin airfoil theory, the section lift coefficient is closest to
Answer: C
Thin airfoil theory gives \(c_l = 2\pi\alpha\) with the angle in radians. Here \(\alpha = 5^\circ = 0.0873\) rad, so \(c_l = 2\pi \times 0.0873 = 0.55\). The common slip is to use degrees directly, which gives a value about fifty-seven times too large.
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