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....
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