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August 21, 2012, 08:17
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problem with cl and cd coeffients
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#1 |
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Member
nauman hashmi
Join Date: Jun 2012
Posts: 54
Rep Power: 13  |
hi i am doing a CFD analysis of blended wing body fuselage. i am facing problems in calculation of Cl and Cd of the fuselage. my cl and cd ratio at many angle of attack (up to 36 deg) are around 3. i am using the projected area along z axis for calculation and my geometry is in YZ plane. my all dimension are in meters. i am conducting analysis at mach 0.8 and 30000 feet altitude. need urgent guidance on this regard.
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August 21, 2012, 08:40
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addtions
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#2 |
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Member
nauman hashmi
Join Date: Jun 2012
Posts: 54
Rep Power: 13 |
my analysis is 3d and i m using SA model for the analysis.
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August 22, 2012, 02:29
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#3 | |
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Senior Member
Join Date: Mar 2011
Location: Germany
Posts: 552
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August 22, 2012, 02:55
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re
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#4 |
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Member
nauman hashmi
Join Date: Jun 2012
Posts: 54
Rep Power: 13 |
no sir they are not matching with the wind tunnel test. like i am gettting Cl value of 0.35 and cd around 0.05. which i think are not correct.
regards |
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August 22, 2012, 03:05
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one more query
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#5 |
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Member
nauman hashmi
Join Date: Jun 2012
Posts: 54
Rep Power: 13 |
sir the cl /cd ratio is around 3 at different angle of attacks. it is just a lifting fuselage not with out wings. moreover the cd calculated by fluent is total cd or some sub set of Cd?
regards |
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August 22, 2012, 07:12
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#6 |
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New Member
Tapan Shah
Join Date: Feb 2012
Posts: 5
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check if ur CV is big enough...
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August 22, 2012, 07:41
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#7 | ||
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Senior Member
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Location: Germany
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