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November 26, 2005, 01:07
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Lift coefficient
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#1 |
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Guest
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I'm calculating airfoil flow. and I set airfoil's angle of attack zero. and I set flow's angle of attack 7 degree. While doing this calculation, Is Cd,Cl right? Do I convert Cd,Cl? or Just Do I use original Cd,Cl?
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November 26, 2005, 02:57
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Re: Lift coefficient
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#2 |
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Guest
Posts: n/a
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Hi Man, The direction of lift and drag is given by the flow direction, so u have to change. hope this helps bharat
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