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  • Lesson 19 post processing nacaAirfoil

    Posted by CHRISTOPHER S on April 17, 2023 at 3:25 pm

    Hi I tried to calculate the drag coeffieicnt and force on the wing but it is coiming as o for all iteration kinldy help me in solving the challeges. I tried with varying the patches name also but nothing is working out

    Barış Bicer replied 1 year, 2 months ago 2 Members · 13 Replies
  • 13 Replies
  • Barış Bicer

    Moderator
    April 17, 2023 at 10:38 pm

    post there the forces and forceCoefficient setup files which are located in /system folder please

  • CHRISTOPHER S

    Member
    April 18, 2023 at 1:13 am

  • CHRISTOPHER S

    Member
    April 18, 2023 at 1:15 am

  • CHRISTOPHER S

    Member
    April 18, 2023 at 3:07 am

    i found this error while running

  • Barış Bicer

    Moderator
    April 18, 2023 at 9:45 pm

    you patches in forceCoefficient file are wrong. What are your patches’ names? can you post /constant/polyMesh/boundary file here!

  • CHRISTOPHER S

    Member
    April 19, 2023 at 12:00 am

  • CHRISTOPHER S

    Member
    April 19, 2023 at 12:01 am

  • CHRISTOPHER S

    Member
    April 19, 2023 at 12:01 am

  • CHRISTOPHER S

    Member
    April 19, 2023 at 12:02 am

    I tried with adding patch name as forceCoeffsCompressible but it is not working out

     

     

  • CHRISTOPHER S

    Member
    April 19, 2023 at 12:04 am

    I tried with adding patch name as forceCoeffsCompressible but it is not working out

     

     

  • CHRISTOPHER S

    Member
    April 19, 2023 at 12:05 am

  • CHRISTOPHER S

    Member
    April 19, 2023 at 12:07 am

    I tried with same patch name as given in the forcecoeffscompressible flow but it is not coming

     

  • Barış Bicer

    Moderator
    April 20, 2023 at 10:14 pm

    come on your patch name is aerofoil dont you see that in boundary file. put this name for both forceCoefficient and force files as patch name then it will work

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