cfd simulation of an uav
 

i've been working on an uav model with a span of around 2m and fuselage lenght around 1m. the inlet velocity(as per the experimental results) is 21m/s.
the results for Cl are matching closely for lower angle of attack, but the problem is i'm not able to get the right stalling angle. i've generated an unstructured mesh(with prism layers) with around 1.2 million elements using ICEM. i've used k-omega turbulence model, also i've done an itterative convergence study for one case. also as a further part of my work i would like to carryout fluttering analysis for the wing, which needs moving mesh. as i'm new to this please suggest what work should i carry out further....?

Capturing the stall point is tricky. Have a look in the literature to find out how other simulation researchers do it. It is not my field so I do not know.

ya i'm already working on it. i'm try now for a structured mesh, this will help me have a better control over the problem. but for analyzing a flutter problem for the airfoil i'll have to generate moving mesh. can you please suggest me on this, it would be really helpful.

Getting closer to the stall point the steady state results won't match with experimentals, because of transient effects (growing vortex shedding etc). Switching to transient solver can handle this problem. I would use adaptive time step to speed up the simulation.
In flutter I have no experience also, but this is good challenge in cfd :)

i havent tried with the transient solver, but will it be effective even for lower velocities (around 22m/s). and more over i've used an unstructured mesh(tetra) will it be advisable to go for structured mesh for higher angle of attack.....? :)

i don't think so...
post pictures of your mesh!

pictures of my mesh
 

ya certainly, i'll mail them to u. thanks a lot for ur suggestions. :)

sir could i please get your email id....... so that i can mail u the contours and other details.

if you are able to do, post pictures here because other people can see it.

i would have certainly posted them here, but i cannot upload attachments in the threads. i feel its not permitted to upload attachments. so it would be helpful if u could give me your email id. looking forward for your reply.:)

felfoldi.attila@gmail.com but try upload here if you can. maybe you should delete the cookies if you have problems with the site.

further improvements
 

i have been successful in getting the stall angle and the Cl is matching quite well with the experimental results. what further improvements can be done on the problem....? i've been thinking of drag reduction using winglets but i dont have the data for the specific winglet. what further improvements can be done.....?

mr prshet,
can you share with me how have you been successfully getting the stall angle? i believe i had the same problem with u.

ya certainly..... can u tell me the mesh details.....? and wht r ur inlet conditions......? if u pls let me know i would be able to help u....

i`m using unstructured mesh of tetrahedral volume on my rectangular domain. my inlet boundary condition was set to be a subsonic flow velocity with Cartesian velocity value. the turbulent intensity was 5%. my inlet was assign at left and bottom face. do you need more info pls tell me.

ya thats alright....wht abt ur geometry.....? hw have u placed it.....? have u considered the whole geometry or only the half part (symmetry). and for different angle of attacks are u moving ur geometry.....?

yes my geometry was taking the simplification of symmetrical condition (half part) and my angle of attack changes were determine by cartesian velocity components define at the inlet. i was not moving my geometry angle at all. what else i shoud do to get a good stall angle prediction?

when u give the Cartesian velocity components it might give u comparable results for lower angle of attack. if u have to capture the stalling angle then it would be better if u manipulate the geometry itself....pls try once.... when u rotate the geometry please keep in mind the change in conditions for ur inlet velocity. this time u dont have to give the u and v components. u simply have to give the u component.

i will look for forward to do it. thanks a lot. but do i need to switch into transient simulation for high AOA (17-20 degree) in order to capture better stall prediction? i have gone through a lot of discussion in this forum. many people suggest transient simulation for stalling prediction.

Wing flutter is an example of fluid-structure interaction (FSI). You should look at the FSI tutorial in CFX help.