Question: For certain aerofoil at given point on the upper surface of the aerofoil, the pressure coefficient is - 0 . 2 7 at very low

For certain aerofoil at given
point on the upper surface of
the aerofoil, the pressure
coefficient is -0.27 at very low
speed. If the free stream Mach
number is 0.75, calculate CP
and Cm at this point

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