Important Information
Geometry
An updated version of the geometry (i.e. iges file 'RSW without Splitter plate') is provided below and recommended for use to those generating their own grids. This version of the geometry deletes the splitter plate and extends the wing to the tunnel wall, increasing the wing span from 48 to 55 inches. The wing is attached directly to the wall, which is to be modeled as a viscous surface.
The RSW geometry as tested in the wind tunnel had a wing which was 48 inches in span mounted to a small splitter plate whose face was 7 inches of the tunnel wall. Preliminary steady state CFD analysis showed that the splitter plate had no effect on the pressure distribution on the wing at the span station of the pressure transducers where the experimental data was collected. The splitter plate has been eliminated from the geometry in favor of extending the wing span from 48 to 55 inches. The wing is still in the same geometric location as it was tested in the wind tunnel, relative to the wall. The elimination of the splitter plate reduces gridding complexities.
An updated version of the unstructured grids reflects the wing span change to 55 inches. The grids with 48 inch wing span are still provided but not recommended.
IGES files
RSW without Splitter plate
RSW with Splitter plate
Airfoil coordinates can be found at: https://c3.ndc.nasa.gov/dashlink/resources/295/
Grids
After discussions by the organizing committee, and some research using the RSW grids, a modification has been made on the RSW grids. The inflow boundary has now been moved so that it is located 1000" in front of the model to provide a more accurate simulation of the boundary layer along the wind tunnel wall. The boundary layer thickness along the wind tunnel wall at the model/wing location should be approximately 12 inches.
Recommended 55 inch wing span grids with the modified inflow boundary location and wing attached to a tunnel wall considered to be viscous. Grids generated using SolidMesh at Georgia Tech.
|
Element |
Resolution |
Node or Cell based |
Link |
Unstructured |
Mixed and Fully Tet |
Coarse/Medium/Fine |
Node |
|
Unstructured |
Mixed and Fully Tet |
Coarse/Medium/Fine |
Cell |
Recommended 48 inch wing span grids and wing attached to a wall considered to be a symmetry plane. Grids generated using ICEM CFD/ ANSYS.
|
Element |
Resolution |
Node or Cell based |
Link |
|
Coarse/Medium/Fine |
55 inch wingspan grids, NOT recommended for AePW comparative analyses
|
Element |
Resolution |
Node or Cell based |
Link |
Unstructured |
Mixed and Fully Tet |
Coarse/Medium/Fine |
Node |
|
Unstructured |
Mixed and Fully Tet |
Coarse/Medium/Fine |
Cell |
|
Structured |
Hexahedral |
Coarse/Medium/Fine |
Hexahedral |
48 inch wing span grids, NOT Recommended for AePW comparative analyses
|
Element |
Resolution |
Node or Cell based |
Available link (will be available soon) |
Unstructured |
Mixed Element |
Fine |
Node |
|
Unstructured |
Mixed Element |
Medium |
Node |
|
Unstructured |
Mixed Element |
Coarse |
Node |
|
Unstructured |
Fully Tet |
Fine |
Node |
|
Unstructured |
Fully Tet |
Medium |
Node |
|
Unstructured |
Fully Tet |
Coarse |
Node |
|
Unstructured |
Mixed Element |
Fine |
Cell |
|
Unstructured |
Mixed Element |
Medium |
Cell |
|
Unstructured |
Mixed Element |
Coarse |
Cell |
|
Unstructured |
Fully Tet |
Fine |
Cell |
|
Unstructured |
Fully Tet |
Medium |
Cell |
|
Unstructured |
Fully Tet |
Coarse |
Cell |
Experimental data for comparison
Experimental Results, in tecplot format, with bad data points removed (both steady and unsteady results are contained in this zip file)
Unsteady results are Frequency Response Functions of pressure coefficients due to oscillatory angle of attack, where angle of attack is in radians.
Unsteady results are presented in both rectangular form (Real and Imaginary components) and polar form (Magnitude and Phase).