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Old   July 21, 2011, 10:32
Default Laminar zone
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Freddy S
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Hello at all,

I have a problem evaluating a calculation I performed!

I am currently modelling a flow around a wing section. Due to low reynolds numbers, a laminar zone occurs. The laminar turbulent transition is well-known from experimental data. Simulating these experiments using a laminar zone (rest: k-e realizable), a comparably good accuracy occured (in lift as well as in drag).

Certainly, at huge angles of attack, the resulting maximum lift coefficient seems unrealistic (huge) due to huge feasible angles of attack before the flow separates. Modelling a turbulent flow (at same adjustments), lift coefficient is less due to less maximum angle off attack (turbulent separation at trailing edge).

Regarding pressure distribution, there is a difference, especially at the section of laminar zone.

Does anyone knows, why such a difference occurs.

Thanks
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Old   July 22, 2011, 08:24
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Raashid Baig
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See this thread below it will give valuable inputs to your problem -

Gamma Theta model and underpredicted lift
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Old   July 22, 2011, 08:34
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neema
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Hi

I am new to this forum, new to CFD and also programming. My first cfd code was jos stam's fluid dynamics code. I came to know it's not a good code to simulate turbulent flow (or is there a way to introduce turbulence into it) . I came to know that RANS is one good method to simulte turbulent flow. It would be very helpful if you could suggest any basic RANS source code I can refer............. Please Help .......
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Old   July 22, 2011, 14:11
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Nik
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@ Above - start with k-e model available in Fluent
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