Hello everyone,
I recreated the NACA0008 profile based on a dataset from UIUC and the result has a 0.2% error with the theoretical value from Vergas et al. (photo 1), when it is under an aoa of 0 degree, and Re of 2000.
However, when I try with an aoa of 4 degrees, with the same model and the same meshing, the coefficients are not at all correct. I adjusted all the components by following an article called “Parametric angle of attack (aoa) study for airfoil lift and drag calculation” on the SimScale forum and used the results from its calculator (photo 2), and the coefficient of lift (around 0.0355) is incorrect but it is pretty good for drag (0.0806). Here are my settings and relevant photos. I would really appreciate any kind of help.
