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Showing results 1 to 5 of 5 Search took 0.00 seconds. Search: Posts Made By: mihaipruna

Forum: OpenFOAM Running, Solving & CFD April 4, 2012, 13:10

Replies: 56 simpleFOAM NACA0012 (α=8°) cL, cD not matching published data Views: 18,907 Posted By mihaipruna that would be nice, but if you look at the two... that would be nice, but if you look at the two files, the L and A ref are the same.

Forum: OpenFOAM Running, Solving & CFD April 4, 2012, 09:13

Replies: 56 simpleFOAM NACA0012 (α=8°) cL, cD not matching published data Views: 18,907 Posted By mihaipruna Joe, I need to use simpleFoam but I would like to... Joe, I need to use simpleFoam but I would like to compare my results with,preferably, published laminar airfoil data for validation. Alternatively, I can use xfoil to get more realistic turbulent...

Forum: OpenFOAM Running, Solving & CFD April 3, 2012, 10:20

Replies: 56 simpleFOAM NACA0012 (α=8°) cL, cD not matching published data Views: 18,907 Posted By mihaipruna That is understood, and I'm only looking for a... That is understood, and I'm only looking for a reasonably accurate Cl and Cd.

Forum: OpenFOAM Running, Solving & CFD April 3, 2012, 09:29

Replies: 56 simpleFOAM NACA0012 (α=8°) cL, cD not matching published data Views: 18,907 Posted By mihaipruna Hi Joe, I used the example here: ... Hi Joe, I used the example here: http://www.dur.ac.uk/g.l.ingram/download/SolidWorksAerofoilGuide.pdf I was assuming that since the static pressure is set to 0 and the flow is incompressible,...

Forum: OpenFOAM Running, Solving & CFD April 2, 2012, 21:00

Replies: 56 simpleFOAM NACA0012 (α=8°) cL, cD not matching published data Views: 18,907 Posted By mihaipruna I have a similar problem, I am trying to analyze... I have a similar problem, I am trying to analyze the NACA 5012 airfoil and getting a Cl of 0.52 at 0 degrees AOA and 15 at 5 degrees AOA! I am hoping that with the low airspeed we are still in the...

Showing results 1 to 5 of 5

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