Estimate the lift and the pitching moment coefficient

Reference no: EM131515111

Question: The pressure distribution over a section of a two-dimensional wing at 4 degrees of incidence may be approximated as follows: Upper surface: C_p constant at -0.8 from the leading edge to 60% chord, then increasing linearly to +0.1 at the trailing edge. Lower surface: C_p 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.

Reference no: EM131515111

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