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  • Lesson 19 post processing nacaAirfoil

    Posted by CHRISTOPHER S on April 17, 2023 at 4:07 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 · 1 Reply
  • 1 Reply
  • Barış Bicer

    Moderator
    April 17, 2023 at 10:37 pm

    Hi,

    Could you tell me how did you try to calculate? If you used run-time post processsing post here your ForceCoeff file which is located inside /system folder. and then simply post here log file of some iteration.

    Then I will try to help you

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