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Reference Values for Air-Foils with high Angle-of-Attack?

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Old   January 9, 2010, 12:11
Default Reference Values for Air-Foils with high Angle-of-Attack?
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I'm still not 100% sure, whether or not I'm setting up the reference values right.
when I have an air-foil with a high angle of attack (eg. 30) what do i have to put in fo area, length and depth?

I'm working with a 2D model and for small angles I take the chord line from nose to tail as the length. and when I want to get the drag properties, i will put in the area normal to the flow.
when I want to get the lift properties I will put in the area parallel to the flow (not the wet surface area, only the projected area).
as far as I know the depth can be 1 because all properties are calculated for one unit and that's also one (in my case) meter.
but when I calculate both properties for x and y / drag and lift and calculate the resulting vector for this (x^2+y^2)^0.5 they aren't near to the values given in references.

does anyone know what I'm doing wrong?

Thank you in advance,

hornig is offline   Reply With Quote


drag coefficient, lift coefficient, reference-values

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