Fluids

Fluids

Airfoil CL & CD Start at normal magnitude then skyrocket.

    • t_top
      Subscriber

      I'm working with a few airfoils, NACA 23012, NACA 63015A, NACA 4412, RC4-10, and Boeing VR-7, analyzing the lift, drag and moment of each.


      Currently working on the NACA 63015A. Using velocities(mph) with their respective lift/drag/moment coefficients are below.

      • 25mph {-0.900/0.0257/0.0225}
      • 50 {-3.7196/0.881/0.0856}
      • 75 {-8.507/0.182/0.1837}
      • 100 {-15.368/0.30669/0.3003}
      • 125 {-24.249/0.4598/0.444}
      • 140 {-21.468/1.4205/0.8104}
      • 150 N/A
    • Karthik R
      Administrator
      Hello,nFirstly, there is an abrupt jump in your mesh just beyond the trailing edge.nSecondly, please check if Reference values. Force coefficients use reference density, velocity, and area. Please check these values (especially when you are comparing with literature). Also, check if your directions are specified correctly.nRegarding the contour plot, please deselect the 'Fluid' region when you are plotting the contour. Deselect everything when you are plotting the contour plot.nHere is an example from our Ansys Innovation Courses which shows how to set-up an airfoil problem.nI hope this helps.nThanks.nKarthikn
    • t_top
      Subscriber
      Hi Kartik,nnThe x spacing in the mesh at the trailing edge changes but the y stays the same. I checked the mesh and it didn't give me any errors.nThe changes in the reference values was the problem with the 63015a airfoil at 10 degrees. I'll try this on the other AoAs and airfoils and will come back to tell you if it worked.nnnThank you!n
    • Karthik R
      Administrator
      Sure thing! Please let me know here is this worked for you.nThank you.nKarthikn
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