Learning Forum

[Nehal97]

I was trying to simulate a 2D NACA 4412 airfoil through Ansys Fluent and I have come across the following problem. After generating the mesh it shows that one of the entities cannot be meshed properly. When I went to check the problematic geometry it is the lower part of the airfoil, as you can see from my added image. 

• In Design Modeler, I have created six different faces to attempt a structured mesh
• I have done edge sizing and made sure to keep the behavior 'Soft' along the straight lines connecting the airfoil but the airfoil edge itself has 'Hard' behavior
• I have followed a bias factor and made sure to reverse bias the lines along the airfoil surface to make sure that there are more divisions near the airfoil

Despite all these, the meshing is shown to be improper. I have tried the following to fix this

• Created separated Edge Sizing for the two airfoil surfaces. One for the upper airfoil and the edge of the C-type domain on top of it with a number of divisions of 120 and 'Hard' behavior. Another one for the lower airfoil and the edge of the C-type domain beneath it with a number of divisions of 150 and also 'Hard' Behavior
• Tried using a different bias factor
• Tried changing the number of divisions to 100 for all the edge sizing

I have checked previous problems related to map mesh control failing to map mesh in this forum, as instructed there I have maintained the Physics Preference to CFD and Solver Prefence to Fluent. The edge sizing has also been done separately. Yet, I am facing this problem. Can anyone please suggest to me what should I do next? I really need help to solve this problem,

[Rob]

What order did you mesh the faces in? I'd also be very wary of running a mesh like that given the jump in cell size. I don't generally run aero models but generally favour pave meshes.