3d Airfoil... NB!!!!!
Please can someone help me...
I am the university of kwa zulu natal and need to model a plane that has circular wings - .ive drawn my 3d wing in PRO/E and imported it into GAMBIT and created the mesh surrounding this part. When i analyse it in FLUENT i get a very low coefficient of lift of about 0.05 - whereas a normal 2D clarkY airfoil is about 0.4. Can anyone take me through the steps i need to do in order to get accurate results...for example reference values, Boundary Conditions, Models.... |
Re: 3d Airfoil... NB!!!!!
Hello mate,
I would start with checking your reference values i.e. Area etc first. Suggest you ask your IT Admin in the department to let you have access to www.Fluentusers.com - lots of stuff on this topic there. |
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