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Above is the image of the question I want to ask. Please clarify on how the pressure coefficients of the upper and lower surfaces of an airfoil can be used, also if there is a set equation to calculate this lift coefficient.

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  • $\begingroup$ The exact way to calculate was not provided. Just wanted to know how it would be calculated. @Bianfable $\endgroup$
    – user2274
    Dec 2, 2021 at 11:44
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    $\begingroup$ Maybe the discussion in this Q&A helps: How are Cd and Cl calculated from Cp data? $\endgroup$
    – Bianfable
    Dec 2, 2021 at 11:52
  • $\begingroup$ I have looked through that discussion, but I can't seem to use the Xfoil software @Bianfable $\endgroup$
    – user2274
    Dec 2, 2021 at 11:58

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