Aerospace Engineering > GATE 2012 > Compressible Flow
The critical Mach number of an airfoil is attained when
A
the freestream Mach number is sonic.
B
the freestream Mach number is supersonic.
C
the Mach number somewhere on the airfoil is unity.
D
the Mach number everywhere on the airfoil is supersonic.

Correct : c

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