Xflr help required!

[Shedofdread]

I've been using Xflr for a little while, both for wing and profile design but I've run into a problem - I need to find the critical Reynolds number for an airfoil.

How do I do this?

Thanks in anticipation,

S

[Windsoarer]

Select the Type 4 polar for airfoil analysis. Then plot Cl vs Re.
The critical Re is the point where Cl drops sharply

Cheers

[Shedofdread]

Many thanks W. Without definitions in the PDF manual, I didn't know what the various graph types were.

S

[Shedofdread]

Sorry to ask so many questions, but I've just run a type4 analysis and the output graph was Cl/Cd versus alpha. What am I doing wrong?

If it is any help, I'm using v413

Thanks again,

S

[Windsoarer]

In the polar view, right click on a graph then select Graph, Variables, and finally choose Re vs. Cl

[Shedofdread]

W - thanks for that. I feel a bit 'dim' not spotting that one.

Job sorted now, got answer.

Thanks again,

S