Discussion
Assertion (A): Sweeping a wing back raises the Mach number at which drag divergence occurs.
Reason (R): Only the velocity component normal to the leading edge governs the section's behaviour.
Select the correct answer from the options below.
Answer: B
Both are true and the second explains the first. That component is smaller than the free stream by the cosine of the sweep, so the section behaves as though flying more slowly and the local supersonic pocket appears later. Every high-subsonic transport is built on this single result.
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