Not in FLUENT
Angle of attack is not known?
Just need to know the normal force and tangetial force from which aoa has to be calculated
Normal force = lift
Tangential force = drag
in that case aerfoil should be aligned with axis, like chord line should be along the axis, then only ur answer will be correct bro
Using Lift ,drag and angle of attack calculate the normal and axial force.
Get the lift and drag value in all points in xl sheet and use the relation between lift and normal force along with angle of attack..
bro, Angle of attack is unknown, as the blade is twisted and tapered
In the Ansys post-processor you need first to define a local coordinate system that is aligned with the fluid flow, then use the force function to find the lift and drag forces in this case.
What is your application (wing or rotor)?
Rotor
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