How to extract the section lift coefficient of the wing in wing.jl #61
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Replies: 3 comments 3 replies
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Hi Inseo, Please see the full example under |
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Hi Ed. Thank you for your reply. The I had already check the validation case that you told me, Thank you. In specific, I want to extract the data type of the sectional lift coefficient(cl) like this. for example, Span position 2y/b 0.0 0.2 0.4 0.6 0.8 1.0 Like this data type(*.dat, *.txt, else.)(not a plot sorry...). Is there way to extract raw data of the sectional cl or cd in code ? Thank you. |
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Yes, you can save the data that you are plotting in any format you would like. You can simply print it to a text file, or save it as a CSV. |
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Here is the exact line where things get plotted: LINK. Instead of plotting, you can save
cl
andcd
to a file.