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-   -   3d wing analysis in fluent !! urgent help . beginner (http://www.cfd-online.com/Forums/fluent/99459-3d-wing-analysis-fluent-urgent-help-beginner.html)

sam15 April 3, 2012 23:34

3d wing analysis in fluent !! urgent help . beginner
 
I am doing a 3d wing analysis
of a wing with chord 30 cm and span 40 cm . I have completed the
meshing in gambit now i want ot do analysis in fluent.
My flow speed is 50 m/sec, RE= 1.01* 10^6(turbulent flow). please tell me the
1- which solver i use??
2-which viscous model??
3- boundary conditions ??
4- how do we get the lift and drag values in fluent after iteration??

I am a basic user . I will be thankful to u.

Zigainer April 4, 2012 07:56

Have you done any tutorial (e.g. "Modeling External Compressible Flow")?

And start reading the manual! Your question are really basic and if you don't know why you choose this and that BC/viscous model, you have no idea of what you get in the end and if the results are reasonable!

-----
1. pressure-based
2. maybe the Spalart-Allmaras model or k-w SST Transitional
3. pressure inlet - pressure outlet
4. -> manual

sam15 April 5, 2012 21:35

hey thanks ............. i applie d all the conditions and iterated it...........but i am not getting the stalling point on the wing............

aqstax April 6, 2012 02:56

Have you tried the tutorials from cornell?

kdrbrk April 11, 2012 10:49

Try velocity values on the surface, and where it goes to negative from positive, than you can understand that flow detaches from surface and reverse flow happens.

aqstax May 25, 2012 00:30

You don't need to use velocity for that. Just look at shear stresses on surface. Where it is 0 is where detachment has occurred.

hannah72206 June 21, 2012 14:21

You should be able to change the angle of attack by rotating the geometry in Design Modeler. Then run that rotated design through the solver and when your lift coefficient starts going down, you know you've reached your stall angle.

hhh August 3, 2012 06:01

velocity inlet in fluent
 
Dear friends,
In fluent, For analysis of 2D naca0012 airfoil velocity inlet we give vcostheta in x component & vsintheta in y component, v is inlet velocity.

1)here i start analysis of 3D wing, for that i take naca 0012 airfoil chord '1'& extrude 100mm, in gambit and analysis in fluent i have doubt how to set velocity inlet, here i consider my velocity is 3m/s, then what is xyz component in inlet velocity boundary condition,please let me know.

2)if you consider 3D wing, (vtantheta for z component) is correct or wrong, please let me know.

2) how to find angle of attack for 3D wing? please let me know


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