2D Airfoil Analysis using Flotran
2D Airfoil Analysis using Flotran
(OP)
Can anyone tell me how to get realistic drag values using Flotran to analysze an airfoil. When I do the surface integral on the airfoil, the lift I am getting seems to be very accurate but the drag has negative values.....any sloutions???





RE: 2D Airfoil Analysis using Flotran
RE: 2D Airfoil Analysis using Flotran
RE: 2D Airfoil Analysis using Flotran
Check your UCS once again.
The X axis has to be parallel to the cord and Y perpendicular to it, facing upwards. It is a good idea to place the airfoil so that the leading edge has (0,0,0) coordinates. This way the X axis is right on the cord.
Also, are you using the intsrf,pres command for the integration of pressure along the airfoils surface (for the lift & drag calculations), or the intsrf,tauw command of the integration of shear stress (also used for the drag calculations in viscous flow)?
I hope this will help
gkoz