Discussion
Assertion (A): Shock-induced boundary layer separation is a serious problem on transonic wings.
Reason (R): The shock imposes a sharp adverse pressure gradient on already slow near-wall fluid.
Select the correct answer from the options below.
Answer: A
Both are true and the second is the reason for the first. The boundary layer has little momentum to spend against a steep rise in pressure, so it thickens and often separates, causing buffet, a loss of lift and a sharp rise in drag. Supercritical sections are shaped largely to keep that shock weak.
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