Rectangular Supercritical Wing

Information Package for RSW

InfoPkg

Documentation of tests conducted at NASA TDT of Rectangular Supercritical wing test in the 1980's and documented in RTO Report 26. More results are also published in other references. Time history data for this test (TDT Test number 353) is not available.

Geometry

https://c3.ndc.nasa.gov/dashlink/resources/295/

Airfoil Shape & Coordinates ( compares different supercritical wing planforms)

IGES file

Modifications to Gridding and 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.

RSW without Splitter plate

RSW with Splitter plate

Grids Provided by Organizing Committee

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	Available link (will be available soon)
Unstructured	Mixed and Fully Tet	Coarse/Medium/Fine	Node	https://c3.nasa.gov/dashlink/resources/502/
Unstructured	Mixed and Fully Tet	Coarse/Medium/Fine	Cell	https://c3.nasa.gov/dashlink/resources/502/

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	Available link (will be available soon)
	Coarse/Medium/Fine		https://c3.nasa.gov/dashlink/resources/530/

55 inch wing span grids (Not Recommended for AePW)

	Element	Resolution	Node or Cell based	Available link (will be available soon)
Unstructured	Mixed and Fully Tet	Coarse/Medium/Fine	Node	https://c3.nasa.gov/dashlink/resources/462/
Unstructured	Mixed and Fully Tet	Coarse/Medium/Fine	Cell	https://c3.nasa.gov/dashlink/resources/463/
Structured	Hexahedral	Coarse/Medium/Fine	Hexahedral	https://c3.nasa.gov/dashlink/resources/468/

48 inch wing span grids (Not Recommended for AePW)

	Element	Resolution	Node or Cell based	Available link (will be available soon)
Unstructured	Mixed Element	Fine	Node	https://c3.nasa.gov/dashlink/resources/419/
Unstructured	Mixed Element	Medium	Node	https://c3.nasa.gov/dashlink/resources/416/
Unstructured	Mixed Element	Coarse	Node	https://c3.nasa.gov/dashlink/resources/414/
Unstructured	Fully Tet	Fine	Node	https://c3.nasa.gov/dashlink/resources/418/
Unstructured	Fully Tet	Medium	Node	https://c3.nasa.gov/dashlink/resources/417/
Unstructured	Fully Tet	Coarse	Node	https://c3.nasa.gov/dashlink/resources/415/
Unstructured	Mixed Element	Fine	Cell	https://c3.nasa.gov/dashlink/resources/441/
Unstructured	Mixed Element	Medium	Cell	https://c3.nasa.gov/dashlink/resources/440/
Unstructured	Mixed Element	Coarse	Cell	https://c3.nasa.gov/dashlink/resources/438/
Unstructured	Fully Tet	Fine	Cell	https://c3.nasa.gov/dashlink/resources/442/
Unstructured	Fully Tet	Medium	Cell	https://c3.nasa.gov/dashlink/resources/439/
Unstructured	Fully Tet	Coarse	Cell	https://c3.nasa.gov/dashlink/resources/437/

Experimental Results for Comparisons

RSW_AePW_expdata_Feb10_2012.ZIP

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 coeffients 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).

RSW_BadDataAssessment.zip

Tecplot files comparing the with and without transition strip information. These data sets were used to determine that all 4 sensors on the upper surface at x/c = .32 were malfunctioning during the runs pertinent to AePW (transition strip on). The file also shows the lower surface sensor at span station 3, x/c = 0.44, which was declared non-functional by the RSW test crew.

Finite Element Model (not applicable)

References

NASA-TM-85673.pdf

Geom.and Str. Properties of a Rectangular Supercritical Wing Oscillated in Pitch for Measurement of Unsteady Transonic Pressure Distributions, Ricketts, Watson, Sandford, Seidel - Nov 1983 (Ricketts)

AIAA-JA_vol21_no8.pdf

Transonic Pressure Distributions on a Rectangular Supercritical Wing Oscillating in Pitch, Ricketts, Sandford, Seidel, Watson, JA Vol 21 No 8, 1983

1999046117.pdf

Computational Test Cases - early RSW (Ricketts - in RTO publicaton) - Complete results are in NASA TM 85765 - Subsonic and Transonic Unsteady- and Steady-Pressure Measurements on a Rectangular Supercritical Wing Oscillated in Pitch by Ricketts, Sandford, W

https://c3.ndc.nasa.gov/dashlink/static/media/publication/TR-026-ALL.pdf