TEST CASES
3rd
AIAA CFD High Lift Prediction Workshop
The test cases for HiLiftPW-3 are defined in the following document:
For the required test cases, participants are asked to run on at least
one set of grids to be provided by the HiLiftPW Committee (if possible).
The official supplied geometry must be used if/when participants create their own grids, and
self-generated grids must be uploaded to the HiLiftPW Committee.
Geometric Reference Parameters for the NASA HL-CRM (note the geometry is in INCHES):
- Mean aerodynamic chord (MAC) = 275.8 in, located at y=468.75 in
- Wing semi-span = 1156.75 in
- Reference area of the semi-span model = Sref/2 = 297,360.0 in2
- Moment reference center (MRC): x=1325.90 in, y=0.0 in, z=177.95 in
- Note: the y-location for the MRC has been corrected as of 4/29/2020; previously it was listed as y=468.75 in, but
y=468.75 in is the location of the MAC
- An incorrect y-location for MRC makes no difference for the pitching moment, which is the only moment requested
Geometric Reference Parameters for the JSM (note the geometry is in MILLIMETERS):
- Mean aerodynamic chord (MAC) = 529.2 mm
- Wing semi-span = 2300.0 mm
- Reference area of the semi-span model = Sref/2 = 1,123,300.0 mm2
- Moment reference center (MRC): x=2375.7 mm, y=0.0 mm, z=0.0 mm
Please check periodically for updates, and/or get on the email distribution list by request to
hiliftpw@gmail.com
to be notified directly of any updates/changes.
Return to: High Lift Prediction Workshop Home Page
Recent significant updates:
04/29/2020 - Corrected y-location of moment reference center of the NASA HL-CRM
03/21/2017 - Added geometric reference parameters (copied from Geometries page)
03/02/2017 - Revised Official Test Case Document (there was a typo regarding grid sizes for Case 3)
02/22/2017 - Revised Official Test Case Document (added explanatory note regarding scaling and Re for Case 1a)
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Last Updated: 04/29/2020
