problem with cl and cd coeffients
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.
thanks |
addtions
my analysis is 3d and i m using SA model for the analysis.
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re
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 |
one more query
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 |
check if ur CV is big enough...
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