GATE AE 2026 AE Q29: Airfoils and Wings

Which of the following statements is/are TRUE regarding critical and drag divergence Mach numbers of a wing?

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Critical Mach number is the minimum freestream Mach number for which sonic condition is attained somewhere over the wing

Drag divergence Mach number is always higher than the critical Mach number

Drag divergence Mach number is the local Mach number over the wing at which the drag increases drastically

Critical Mach number is independent of the angle of attack

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