Hi all, I want to ask that while doing 2D analysis of aerofoil what will be tht reference area?. what will be the referance area in setting reference values in Fluent? and also tell the reference length

Thanks

hi, you can give the maximum thickness of the airfoil in the reference area to find lift and drag.

In 2D Aerodynamics you usually use for an airfoil the chord as a reference length. The reference area is obtained using a fictive span of length 1.

Reference area = Chord x Span

where Span = 1 meter if you use SI

If you want more theoretical considerations read the first chapter of Anderson book "Fundamentals of Aerodynamics".