# 3d wing analysis in fluent !! urgent help . beginner

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 April 3, 2012, 23:34 3d wing analysis in fluent !! urgent help . beginner #1 New Member   Dinesh Singh Rawat Join Date: Dec 2011 Posts: 3 Rep Power: 5 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.

 April 4, 2012, 07:56 #2 Senior Member   Join Date: May 2011 Location: Germany Posts: 130 Rep Power: 7 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

 April 5, 2012, 21:35 #3 New Member   Dinesh Singh Rawat Join Date: Dec 2011 Posts: 3 Rep Power: 5 hey thanks ............. i applie d all the conditions and iterated it...........but i am not getting the stalling point on the wing............

 April 6, 2012, 02:56 #4 Member   Abdulqadir Aziz Join Date: Jan 2012 Posts: 45 Rep Power: 6 Have you tried the tutorials from cornell?

 April 11, 2012, 10:49 #5 Member     Burak Join Date: May 2009 Posts: 90 Rep Power: 9 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.

 May 25, 2012, 00:30 #6 Member   Abdulqadir Aziz Join Date: Jan 2012 Posts: 45 Rep Power: 6 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.

 June 21, 2012, 14:21 #7 New Member   Hannah Mac Join Date: Jun 2012 Posts: 15 Rep Power: 6 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.

 August 3, 2012, 06:01 velocity inlet in fluent #8 Senior Member   kunar Join Date: Nov 2011 Posts: 117 Rep Power: 6 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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