|January 9, 2010, 12:11||
Reference Values for Air-Foils with high Angle-of-Attack?
Join Date: Aug 2009
Posts: 12Rep Power: 9
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,
|drag coefficient, lift coefficient, reference-values|
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