Forum
Important Notice for New User Registrations
To combat an increasing number of spam and bot registrations, we now manually approve all new user registrations. While this may cause a delay until your account is approved, this step is essential to ensure the quality and security of this forum.
To help us verify your registration as legitimate, please use a clear name as user name or an official email address (such as a work, university, or similar address). If you’re concerned that we may not recognize your registration as non-spam, feel free to email us at with a request to approve your username.
Airfoil polar Analysis
Greetings,
I’m making an aeroelastic simulation for a Small wind turbine
the turbine uses ” fx 63-137 13.7 smoothed ” airfoil through its entire blade length
i want to get the polars ” Cl , Cd , Cm ” for the turbine , i’m using qblade to perform xfoil analysis
i divided the blade into 30 section and calculated the Reynolds number at the design conditions ( wind speed and rotational speed )
how could i choose the value of reynolds number which input in qblade ? as the reynolds number is not constant along the blade length
Please find the attached with variation of reynolds number with the blade length
Regards,
Uploaded files:- You need to login to have access to uploads.
Hello Ahmed,
for this purpose you can generate a multi-polar blade definition, for which you can assign multiple polars to each blade sections that span over a range of Reynolds numbers (see LINK). This Reynolds number range should cover the whole range of the windspeed-rpm operational data of the modeled turbine.
During a simulation the lift and drag polar data is then interpolated at every timestep to the local Reynolds number of every blade section.
BR,
David
