Discussion
A section has a drag-divergence Mach number of \( 0.72 \) unswept. Swept back \( 30 \) degrees, the wing's drag-divergence Mach number rises to roughly
Answer: C
To a simple approximation the free-stream Mach number may be raised by the factor \( 1/\cos\Lambda \) before the section sees the same normal component, so \( 0.72 / \cos 30^\circ = 0.72/0.866 = 0.83 \). Real wings fall a little short of this estimate, because the simple sweep theory ignores root and tip effects.
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