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Old   March 4, 2011, 12:40
Default cfd simulation of an uav
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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....?
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Old   March 6, 2011, 18:12
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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.
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Old   March 7, 2011, 01:08
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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.
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Old   March 7, 2011, 08:10
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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
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Old   March 8, 2011, 08:56
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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.....?
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Old   March 8, 2011, 11:15
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Quote:
will it be advisable to go for structured mesh for higher angle of attack
i don't think so...
post pictures of your mesh!
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Old   March 8, 2011, 14:10
Default pictures of my mesh
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ya certainly, i'll mail them to u. thanks a lot for ur suggestions.
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Old   March 10, 2011, 10:28
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sir could i please get your email id....... so that i can mail u the contours and other details.
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Old   March 11, 2011, 07:02
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if you are able to do, post pictures here because other people can see it.
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Old   March 11, 2011, 08:30
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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.
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Old   March 11, 2011, 09:03
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felfoldi.attila@gmail.com but try upload here if you can. maybe you should delete the cookies if you have problems with the site.
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Old   March 15, 2011, 12:01
Default further improvements
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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.....?
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Old   May 18, 2011, 04:17
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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.
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Old   May 20, 2011, 03:32
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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....
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Old   May 21, 2011, 02:17
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Quote:
Originally Posted by prshet View Post
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.
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Old   May 21, 2011, 03:54
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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.....?
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Old   May 22, 2011, 06:43
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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?
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Old   May 25, 2011, 10:03
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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.
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Old   May 29, 2011, 20:31
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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.
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Old   May 29, 2011, 22:51
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Quote:
Originally Posted by prshet View Post
but for analyzing a flutter problem for the airfoil i'll have to generate moving mesh.
Wing flutter is an example of fluid-structure interaction (FSI). You should look at the FSI tutorial in CFX help.
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