|January 9, 2010, 12:11||
Reference Values for Air-Foils with high Angle-of-Attack?
Join Date: Aug 2009
Posts: 12Rep Power: 7
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|
|Thread||Thread Starter||Forum||Replies||Last Post|
|OpenFOAM on MinGW crosscompiler hosted on Linux||allenzhao||OpenFOAM Installation||127||January 30, 2009 20:08|
|Two-Phase Buoyant Flow Issue||Miguel Baritto||CFX||4||August 31, 2006 12:02|
|Windows Installation BugsComments on Petrbs patch||brooksmoses||OpenFOAM Installation||48||April 16, 2006 00:20|
|High Angle of Attack||w0er||Main CFD Forum||3||March 8, 2005 12:05|
|Multicomponent fluid||Andrea||CFX||2||October 11, 2004 05:12|