Aerospace Engineering > GATE 2026 > Compressible Flow
Which of the following statements is/are TRUE regarding critical and drag divergence Mach numbers of a wing?
A
Critical Mach number is the minimum freestream Mach number for which sonic condition is attained somewhere over the wing
B
Drag divergence Mach number is always higher than the critical Mach number
C
Drag divergence Mach number is the local Mach number over the wing at which the drag increases drastically
D
Critical Mach number is independent of the angle of attack

Correct : a,b

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