Discussion
Assertion (A): Sweeping a wing raises the Mach number at which drag divergence occurs.
Reason (R): Only the free-stream component normal to the leading edge governs the section's behaviour.
Select the correct answer from the options below.
Answer: D
Both statements are true and the second is the reason for the first. The normal component is smaller than the free-stream speed by the cosine of the sweep angle, so the section behaves as though flying more slowly and reaches sonic conditions later. This is why every high-subsonic transport has a swept wing.
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