The pressure distribution over a section of a two-dimensional wing at 4 degrees of incidence may be approximated as follows: Upper surface: Cp constant at – 0.8 from the leading edge to 60% chord, then increasing linearly to +0.1 at the trailing edge. Lower surface: Cp constant at – 0.4 from the leading edge to 60% chord, then increasing linearly to + 0.1 at the trailing edge. Estimate the lift coefficient and the pitching moment coefficient about the leading edge due to lift.

The lift coefficient is 0.3192 while that of the moment about the leading edge is-0.1306.

Explanation:

The Upper Surface Cp is given as

The Lower Surface Cp is given as

The difference of the Cp over the airfoil is given as

Now the Lift Coefficient is given as

Now the coefficient of moment about the leading edge is given as

So the lift coefficient is 0.3192 while that of the moment about the leading edge is-0.1306.

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