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Winglet analysis HELP

    • Ratchanon Roongroje
      Subscriber

      My Cd and Cl values seem to be incorrect. The airfoil model used is BAC449 which should gives Cd of 0.07 and Cl of 0.25 at zero deg angle of attack. I have tried to increase the mesh resolution and draw wing with another airfoil but both give incorrect values. I guess my setup is wrong. Please help.

      The wb  and Cd&Cl reference are attached below.

      http://airfoiltools.com/airfoil/details?airfoil=bacxxx-il

      https://drive.google.com/drive/folders/1TQ8XeMb1hjFUv4vIMIs_TWITwwnLR3Nk?usp=share_link

    • Rob
      Ansys Employee

      Have you reviewed the NACA tutorials? I suspect you need to read the section on Reference Values. 

    • Federico Alzamora Previtali
      Subscriber

      We would need more information to be able to help you.

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