wing cl and cd

- May 3, 2019 at 3:31 am
  
  veera
  Subscriber
  
  hi gd mrn to all
  
  i am trying to calculate the cl and cd values of wing in ansys fluent , in that reference value setup in fluent for 3d wing , what value i have to give ?, i watched some you tube videos , some one telling for calculating the cl and cd that reference value we have to get from report>projected area ,
  
  but some one using face area from wing ( calculated in geometry design modeler) , some one using surface area of the wingbut i need to know clearly , which area suppose using in reference area , its should match with experimental calculations
- May 3, 2019 at 11:06 am
  
  Rob
  Forum Moderator
  
  It depends on what reference you're comparing with from the experiment. I'd recommend looking at the ANSYS tutorials (under Documentation). You can always get the forces and figure it out from there?
- May 3, 2019 at 11:19 am
  
  Keyur Kanade
  Ansys Employee
  
  check this one
  
  https://confluence.cornell.edu/display/SIMULATION/FLUENT+-+3D+Transonic+Flow+Over+a+Wing
- May 6, 2019 at 5:08 am
  
  veera
  Subscriber
  
  check this one
  
  https://confluence.cornell.edu/display/SIMULATION/FLUENT+-+3D+Transonic+Flow+Over+a+Wing
  
  thank u mr. kkanade ..i learned lot from this videos..but still i have doubt in that one , for monitoring wing cl and cd why they selected wing tip aong with wing surface?
- May 13, 2019 at 10:48 am
  
  veera
  Subscriber
  
  HI , I was noticed one thing (https://confluence.cornell.edu/display/SIMULATION/FLUENT+-+3D+Transonic+Flow+Over+a+Wing) in that they put wing surface are in that reference value to get the solution , but my case suppose i am putting planform area of the wing , then only i am getting results which is closer to the experimental
- May 13, 2019 at 11:12 am
  
  Rob
  Forum Moderator
  
  Can you provide some images (inline) along with areas. As you're looking at coefficients you need to be careful you're comparing like-for-like values, especially with experimental data where we don't necessarily know the reference area/force/whatever.
- May 14, 2019 at 9:45 am
  
  veera
  Subscriber
  
  if you looking above picture , i am getting 0.80744....this is wing face area
  
  but if i am putting planform area 0.4 ..i am getting results
- May 14, 2019 at 2:07 pm
  
  Rob
  Forum Moderator
  
  So, which reference area is correct if you look in the documentation & check against how the experimental data was calculated?
- May 27, 2019 at 3:00 pm
  
  veera
  Subscriber
  
  half of the above wing area , 0.4