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This is a Cp data for NACA0012 with AoA 9 deg. chord c=0.6. use this data to compute lift and drag forces due to pressure.

This is a Cp data for NACA0012 with AoA 9 deg. chord c=0.6. use this data to compute lift and drag forces due to pressure. how i should solve it
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using equation for a symmetrical 4-digit NACA airfoil

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