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I'm looking for some guidance on how to compute the chord-wise lift distribution of the wing using Xflr5 or OpenVsp or any analytical method. This is for designing the internal structure of the wing.

I appreciate any help you can offer.

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  • $\begingroup$ FWIW: To the question "can I obtain the pressure distribution in the chordwise direction for a segment of the wing in XFLR5", this forum answer says yes: "switch to the Cp view (F9) in the 3d module" $\endgroup$
    – mins
    Nov 16 at 19:27

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