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Showing results 1 to 8 of 8 Search took 0.00 seconds. Search: Posts Made By: FelixL

Forum: OpenFOAM February 9, 2011, 12:14

Replies: 16 airfoil study Views: 2,073 Posted By FelixL The nonorthogonal faces shouldn't be that much of... The nonorthogonal faces shouldn't be that much of a problem. I had worse meshes and I was able to get decent results. Could you post some screenshots of your mesh? Like an overview and some details...

Forum: OpenFOAM February 9, 2011, 11:35

Replies: 16 airfoil study Views: 2,073 Posted By FelixL There is a problem with nuTilda, the transport... There is a problem with nuTilda, the transport equation isn't being solved. I'm guessing it's got something to do with the boundary setup, though I don't have any recommendations right now. My...

Forum: OpenFOAM February 9, 2011, 11:12

Replies: 16 airfoil study Views: 2,073 Posted By FelixL To create a logfile, run simpleFoam with a... To create a logfile, run simpleFoam with a command like this: simpleFoam > log & This will create a file called log where all the residual information will be stored. Also simpleFoam will run...

Forum: OpenFOAM February 9, 2011, 10:51

Replies: 16 airfoil study Views: 2,073 Posted By FelixL Care to post the log file of your case? It seems... Care to post the log file of your case? It seems to me that the simulation crashed or something, leading to unphysical results and hence the lift and drag coefficients in the order of 10^10. ...

Forum: OpenFOAM February 9, 2011, 10:08

Replies: 16 airfoil study Views: 2,073 Posted By FelixL Hello, This line tells you the overall... Hello, This line tells you the overall dimension of your computational domain: Overall domain bounding box (-26.0276 -31.0934 -0.823828) (30 29.304 0.823828) The bold numbers are the...

Forum: OpenFOAM February 9, 2011, 09:59

Replies: 16 airfoil study Views: 2,073 Posted By FelixL Hello, reference Area = chord length * wing... Hello, reference Area = chord length * wing span For 2D cases the wing span can be set arbitrarily but it has to be accounted for when calculating the ref area. Use the checkMesh output to...

Forum: OpenFOAM February 9, 2011, 09:43

Replies: 16 airfoil study Views: 2,073 Posted By FelixL The other BCs are looking alright. Are the... The other BCs are looking alright. Are the reference values for calculating the aerodynamic coefficients correct? (ref. area = 1m²) What does checkMesh say? Greetings, Felix.

Forum: OpenFOAM February 9, 2011, 08:38

Replies: 16 airfoil study Views: 2,073 Posted By FelixL Hello, salvoblack, first thing that... Hello, salvoblack, first thing that catches my eye: the freestream values of nutilda are much too high. Values of 3 to 5 times the molecular viscosity are appropriate for external aerodynamic...

Showing results 1 to 8 of 8

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