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October 11, 2010, 08:45 |
Pls help
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#1 |
New Member
Sreedevi Radhakrishnan
Join Date: Oct 2010
Posts: 1
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I want to calculate lift and drag coefficients for a 3D airfoil. My airfoil has got thickness so hope i can consider it as 3D. The angle of attack is 15 degrees so i have resolved the force vectors in solve- monitors-force.
The problem is with Report- Reference values. There what values should be given for area and length? Please help me Thanks in advance |
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Tags |
3d airfoil, reference values |
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