[Daaman]

Hi,

This might be a pretty basic question, but I'm unable to wrap my head around it. I want to calculate the radial thrust and torque loading on the propeller blade using the CFD results from ANSYS Fluent & SU2. The sectional thrust and torque of a twisted propeller blade are a function of - the local angle of attack, local lift, and drag. I can extract the pressure distribution at each spanwise element section and integrate them to compute the local lift at each section. But, for calculating the sectional drag I require the element thickness (airfoil) at the given span, which I don't have. My question is, how can I extract the thickness of the element at a span (for local drag) and the local angle of attack (for final thrust and torque) from the Fluent/SU2 data? For the moment, I am ignoring frictional forces.

Thanks!