swept back wing: how and which boundary conditions to use in Fluent?
 

hey ppl
i am currently doing a project on static and dynamic stability of a swept back wing. So far i have created the wing in Solidworks,exported it to ansys fluent and meshed it. What I am confused with is the next step. Can you tell me the exact boundary conditions to give in fluent?
I would like to find out Cl , Cd and pressure distributions at different angle of attacks

Thanx

I would take some time to read the fluent ansys user and theory manual. Also do some general internet searching I bet you can find a handful of papers that give their boundary condition details. Here is one that popped up on the first search.

http://www.ripublication.com/aasa/aasav3n3spl_02.pdf

thanx a lot for that ...it was very helpful :)
 

thanx a lot for that ...it was very helpful :)
as i am new to this...i may ask some weird questions..dont mind :)
after i run iterations for a certain number of times and close it ..i am not able to view the graphs again after opening it

angle of attack
 

also can you tell me how to plot graph between for pressure distribution when you are varying angle of attack and velocity

operating pressure
 

hi
i am doing an analysis over an aircraft wing in fluent with a mach no 0.785 and would like to know the operating conditions as well as guage pressure to be used in the boundary conditions

Hi
For first question You need to save both case and data of your solution and for next time you should open the *.cas and after that load the *.dat file to check your results.

For second question for each velocity or AOA go to reports and print pressure distribution on your desired boundary condition ( in this case surfaces of wing), now save the value in a spread sheet and repeat the work for all velocities and AoAs and finally plot them.

My suggestion is to read Ansys fluent theory guide and tutorial guide to make the job easier. Found this quickly:
http://www.cfd-online.com/Forums/flu...tml#post481127

thankyou so much for the help...it was very effective:)

FSI analysis
 

i have got a small doubt in FSI analysis..i made my wing and put a rectangular domain region over it..i ran the flow analysis over it and found out pressure distribution over the wing.this pressure i imported to static structural analysis.i then clicked the root of the wing as my fixed support and ran deformation analysis. i think i got the results but the problem is i cant view the wing alone.. it is coming along with the rectangular boundary region.
how can i view the deformation on the wing alone?
i ll attach some files for reference

thanx in advance:):):):):)