Extremely high drag and lift coefficient

- July 12, 2024 at 4:30 pm
  
  Edgar Heng
  Subscriber
  
  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?
- July 15, 2024 at 7:09 am
  
  Essence
  Ansys Employee
  
  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