# RAE2822 airfoil

(Difference between revisions)
 Revision as of 10:13, 16 September 2005 (view source)Praveen (Talk | contribs)← Older edit Latest revision as of 10:59, 16 September 2005 (view source)Praveen (Talk | contribs) Line 10: Line 10: The following results are from a vertex-centered finite volume code which uses [[Spalart-Allmaras model]]. The grid is taken from the [http://www.grc.nasa.gov/WWW/wind/valid/raetaf/raetaf01/raetaf01.html NPARC Alliance web-site] and consists of 23952 vertices and 47104 triangles. The [itex]y^+[/itex] for the nearest vertices is less than 3. The following results are from a vertex-centered finite volume code which uses [[Spalart-Allmaras model]]. The grid is taken from the [http://www.grc.nasa.gov/WWW/wind/valid/raetaf/raetaf01/raetaf01.html NPARC Alliance web-site] and consists of 23952 vertices and 47104 triangles. The [itex]y^+[/itex] for the nearest vertices is less than 3. + + ===Triangular grid and finite volumes=== + + [[Image:Vtc_rae2822_grid.png | Triangular grid and finite volumes]] ===Pressure contours=== ===Pressure contours===

## Latest revision as of 10:59, 16 September 2005

The freestream conditions are:

• Mach number = 0.729
• Angle of attack = 2.31 deg.
• Reynolds number = 6.5 million

## Sample results

The following results are from a vertex-centered finite volume code which uses Spalart-Allmaras model. The grid is taken from the NPARC Alliance web-site and consists of 23952 vertices and 47104 triangles. The $y^+$ for the nearest vertices is less than 3.

### Pressure coefficient

The pressure coefficient on the airfoil surface is compared with experimental results.