Hi everyone, i am analizing a 3D wing that have a naca profile 63412, 0° AoA, velocity 300 km/h..Why when i calculate the lift coefficient (solution -> report definition->lift coefficient->compute) i get a value of 3300? i mean, shouldn't the lift coefficient have a value ranging from 0 to 1.5 more or less? Also the drag coefficient has a high value (205), while the lift force is acceptable (2400 N). Could someone help to understand why of these high value? Thanks
October 21, 2024 at 11:08 am
Rob
Forum Moderator
It's a coefficient. Look at the definition carefully, if you didn't alter the reference values you'll get an unexpected result. Alternatively, check you're using air, water can produce a similar effect! If you check the examples in Fluent's Help there are a couple of NACA wings modelled which will show you how to work with the coefficients.
October 22, 2024 at 7:46 am
francescomarrocco1207
Subscriber
Hi Rob thank you for your answer..i'm using air at sea level, could you link these NACA examples please? i don't find them
October 22, 2024 at 10:47 am
Rob
Forum Moderator
https://ansyshelp.ansys.com/public/account/secured?returnurl=/Views/Secured/prod_page.html?pn=Fluent&pid=Fluent&lang=en and Learning (left tool bar on here).
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