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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Related Topics

aerospace engineering GATE 2026 critical mach number drag divergence mach number GATE aerospace wing aerodynamics freestream Mach number angle of attack drag increase sonic condition

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