|August 10, 2009, 16:08||
Join Date: Apr 2009
Posts: 35Rep Power: 8
I am working on 3D wing analysis, I have modeled a wing and subtracted it from a rectangular volume and meshed it with 1 million cells using Gambit.
To run the simulation in fluent
what boundary conditions should i use?
In post processing, what data i can get from fluent to analyse the performance of wing?
thanks for ur time....
|August 10, 2009, 17:07||
Join Date: Jul 2009
Location: Akron, OH
Posts: 90Rep Power: 9
If your flow is subsonic, the farfield boundaries can all be specified as velocity inlets and the outflow specified as a pressure outlet.
Alternatively, if the flow is trans/supersonic, you will want to specify pressure-farfield boundary conditions for all of the farfield boundaries. Doing so will permit you to specify a mach number and flow direction on those boundaries. The energy equation and ideal gas model must be activated for trans/supersonic flow. The boundary conditions may also be specified in this manner for subsonic flow and should not produced noticebly different results given that the Mach number is small.
See the fluent tutorial from external compressible flow. I believe the geometry is two-dimensional but it will provide a basis for setting your boundary conditions.
With regard to the wing, the boundary condition should be specified as wall. If no viscous model is activated, the walls will be specified with a slip condition automatically.
Postprocessing your model within Fluent:
It is possible to gather lift, drag, and moment coefficients as well as pressure coefficients along the upper and lower surfaces of the wing within Fluent.
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