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July 20, 2010, 08:12
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Cd of Delta wing
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#1 |
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New Member
Ashok
Join Date: Jul 2010
Location: India
Posts: 20
Rep Power: 15  |
Hello,
I was analysing a delta wing ( Span 22 meters, Length 40 meters, Sweep ange 65 degree, and using double delta, notched wing ) in fluent for getting its Cd. But the value of Cd I am getting is around 28 which is very much higher than the actual (actual value of Cd < 1.00 ). Whats happening ? where is the problem ? Please help. Note: I was using K-epsilon model for getting turbulance, and a moving wall condition with a velocity of 2 mach and pressure of 12032 pascals. |
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| coefficient of drag, delta wing |
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