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The local Mach number at a point on the airfoil reaches 1 for critical Mach number.

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The local Mach number at a point on the airfoil reaches 1 for critical Mach number.

(a) True

(b) False

I got this question by my college professor while I was bunking the class.

I would like to ask this question from Critical Mach Number in division Linearized and Conical Flows of Aerodynamics

1 Answer

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Best answer
Right choice is (a) True

Best explanation: For a freestream Mach number, the local Mach number at the airfoil varies based on the pressure distribution. At the upper surface, there is a point with minimum pressure where the local Mach number is maximum. Thus for critical Mach number, this local Mach number at the upper surface of the airfoil is unity.

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