EDIT: I have managed to figure out it out, well most of it. I created a mold in solidworks that served as my domain, and have a hollow section inside, the wing, that serves as a wall for Fluent. I then meshed everything in Design Modeller, then imported that into Fluent The problem I am having...
I have a swept wing that I made in Solidworks and would like to import it into Fluent so I can run some calculations such as lift and drag and various coefficients. For a 2D airfoil is it straight forward, but for a 3D wing it seems a bit more complicated. I have imported the model as a...
Thanks for the help, I'm working on the mesh using tets and I'm getting around 3600 elements and 18000 nodes. The problem is that since the serrations are complex I need more mesh definition on the leading edge and less on the trailing edge, I'll keep working on it
Yes it's very unusual, it's a solid model that will be printed on a 3d printer, so it will be a solid wing. That's the reason I used solid elements to mesh it. There won't be any spars, skin or anything like that.
The thing is that since my airplane wing is a bit more complex. It has a serrated leading edge and an airfoil (not a flat plate) So I thought the only way was to model it as a solid and not a surface with plate elements. Another problem I ran to was since the plate elements need a thickness and...
The reason I want to model it as a solid is because I imported a parasolid model of the wing that I made in solidworks. I would like to import it, mesh it and run some stress analysis on the structure.
I have this solid model of a wing using solid elements and I would like to apply a linear distributed load and eventually a non linear load extending from root to the tip of the wing. I have successfully applied an evenly distributed load from the root to the tip. I simply selected...
I went ahead and created a 10 inch span rectagular solid with a 1.5 chord in solidworks and imported that into femap. I created the mesh, making sure I selectede midside nodes. This time the deflection was 0.61 inches at the tip with a unit load. I did a rough estimate on paper and the...
I have created a solid model of a wing. It is a NACA 0012 airfoil simply extruded for a span of 10 inches and a chord of 1.5 inches. When I imported the model into FeMap as a parasolid, the results of the analysis do not seem to be correct. I believe it is because I meshed it incorrectly. I am...
span: 10 inches
chord: 1.5 inches
I will try and represent it with a simple rectangular solid section and compare the results. By the way, when I select the property on the mesh it asks me to select a plate,shear panel, panel, rod, beam, etc for the element type. I have always selected a...
I have created a solid model of a wing. It is a NACA 0012 airfoil simply extruded along a certain length. When I imported the model into FEMAP as a parasolid, the results of the analysis do not seem to be correct. I believe it is because I meshed it incorrectly. I am getting a unit load...
