A thin airfoil is mounted in a low-speed, subsonic wind tunnel, in which the Mach number is 0.1 . At a point on the airfoil, the pressure coefficient is measured to be -1.2 . If the flow velocity is increased such that the free-stream Mach number is $0.6,$ the pressure coefficient at the same point on the airfoil will approximately be:

(A) -3.5

(B) -2.9

(C) -1.5

(D) -0.75

A thin airfoil is mounted in a low-speed, subsonic wind tunnel, in which the Mach number is 0.1 . At a point on the airfoil, the pressure coefficient is measured to be -1.2 . If the flow velocity is increased such that the free-stream Mach number is $0.6,$ the pressure coefficient at the same point on the airfoil will approximately be:

(A) -3.5

(B) -2.9

(C) -1.5

(D) -0.75

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