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Calculation Lift and Drag of airfoil

    • Milad karimi
      Subscriber

      Hi everyone,

      I am simulating an airfoil that I want to get its performance curve at different angles of attack. I solve its flow steady.

      From an angle of attack of 0-8.5 degrees I get a constant value for lift and drag. If the angle of attack is about 9 degrees, the residuals of the solution as well as the lift and drag graphs that are drawn in Fluent become oscillating. As the angle of attack increases from 9-20 degrees, this behavior still exists.

      Can someone help me what should I do to calculate lift and drag in the range of 9-20 degrees of attack angles?

      Should the flow be solved in the form of transient in this range (9-20 degrees)?

      Regards

      Milad

    • Hemantg_17
      Subscriber

       

       

      Hello  Milad.
      What I deduce from your observations is that stalling, or flow separation may have occurred after the 9 degree angle of attack. To get a better understanding of your problem, please provide the following information:

      1.Aerofoil type.

      2.Images of performance curves (quantities plotted)

      3.Have used the parametric option or entered values manually?

       

       

      • Milad karimi
        Subscriber

        Yes, stall or current separation may occur at angles greater than 9 degrees.

        I have experienced this for many airfoils.

        My question is, in the angles after the stall, to calculate the performance curve of the flow airfoil, should it be solved Steady or Transient?

        I did not understand the meaning of your sentence (3.Have used the parametric option or entered values manually?). Can you say more clearly?

        I manually input the Cos and Sin values of each angle into Fluent.

        • Hemantg_17
          Subscriber

          It is difficult to determine which settings should be used, whether steady or transient and what is the significance of calculating performance curve after airofoil stalls ?? I would recommend going through the courses available on AIS. What I gather from your statement is that you entered AOA values manually. Please do check the parametric option in Ansys Fluent to generate a set of output parameters based on the input parameters(if interested).

        • Milad karimi
          Subscriber

          In which part of Fluent is the "parametric" option and how does it work? (My Ansys is 2022-R1.)

          What features does this option have?

          Please explain more about it and if possible provide a video how to use it to automatically extract the airfoil performance curve and also extract the related contours.

          Regards

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