i have a general question about airfoils lift and drag coefficients. as i know, lift and drag coefficients are function of angle of attack and Reynolds number.usually airfoils lift and drag coefficients are computed in constant Reynolds number(for example ,lift and drag coefficients of airfoil S818 are computed in Reynolds number 4000000).the question that i want to ask is what Reynolds number must be selected for these calculations?
Unfortunately, AeroDyn v15 within FAST v8 does not yet support interpolation of airfoil data based on Reynold’s number. If the airfoils you are using are strongly influenced by Reynold’s number, I would suggest finding the “expected” Reynold’s number at each radial station (based e.g. on omega cross radius) and choosing airfoil data there appropriate to that Reynold’s number.
thank you very much for your brief answer. i wan to know,What is the error due to ignoring the effect of the Reynolds number in Aerodyn 15 and FAST simulation?
I can’t answer your question in general. Some airfoils have coefficients that are strongly dependent on Reynold’s number, while other airfoils have a weak dependence.