Learning Forum

[Edgar Heng]

Im using NACA 2408 , with free stream flow velocity= 1.46m/s. The angle of attack is at 0 degree. 

Ive been following tutorial in youtube to be honest. But when i run the calculation. The drag and lift coefficient shoots up to absurdly high values 

What have i done wrong ? 

Another question, from my school’s work question it stated using : chord= 0.25m , NACA2408, free stream velocity= 1.46 m/s and span = 1m. But when i draw the Aerofoil, i copy the coordinates from the Airfoil tools website. The chord shown is 1m. How should i change the chord?

[Essence]

Hello,

Please check the mesh (quality, refinement and aspect ratio) and the case setup (BCs, models and other necessary settings). Here is the tutorial which may give you a better insight for your application. This issue may also occur if the reference values are not set properly, since reference values are used to determine lift and drag coefficients.

https://ansyshelp.ansys.com/account/secured?returnurl=/Views/Secured/corp/v232/en/flu_tg/flu_tg_oneram6_wing.html