AIAA CFD High Lift Prediction Workshop
Geometry and Mesh Generation Workshop
NASA High Lift Common Research Model (CRM-HL):
Test Article Definition:
A general description of the CRM-HL can be found in
AIAA Paper 2020-2771 (Lacy & Clark).
Specifically, the particular geometry definition
provided here represents the NASA 10%-scale
semispan CRM-HL test article, as tested in the QinetiQ wind tunnel in 2019
(AIAA Paper 2020-2770 (Evans et al.).
However, note that the following geometry files for this configuration are provided in full-scale inches.
The geometry files are provided in both IGES and STEP formats.
There are three landing configurations included.
The first is the nominal configuration, with inboard flap angle of 40 degrees and
outboard flap angle of 37 degrees.
The second and third configurations have modified flap settings: one at 37/34 degrees, and the other at 43/40 degrees.
The Test Cases for HLPW-4 are posted on the
Test Cases page.
- Nominal Configuration (inboard/outboard flap angles on 40/37 deg):
- Inboard/outboard flap angles of 37/34 deg:
- Inboard/outboard flap angles of 43/40 deg:
The V2 geometry is different from V1 in the following way. Pinch-points
(where a CAD face has a very cusp-like corner where two curves meet at nearly 0 degrees)
were adjusted on the flap-bracket connections to the flap underside, and on the outer WUSS end-wall.
The adjustment made the angle slightly more pronounced where the curves meet,
and this corrected some very slight overlaps detected between these curves as they approached the corner.
This fix helps avoid some grid generation issues and also helps to
insure consistency among all grids (many grid generators were found to require adjustments in these regions).
If you encounter any problems/issues as you build grids using the V2 geometry, please make your own
fixes, DOCUMENT everything done, and plan to share your fixes with the workshop committee.
Note that the geometry includes regions that may be very difficult to grid (and possibly solve),
including very thin gaps at the bottom/inside edge of the slats. These were present in the
wind tunnel configuration, so they were left in. It is up to you how to handle such areas;
this is part of the challenge of the workshop. Again, be sure to document every
assumption/change/fix that you make, as your grids are created.
NOTE: STEP files only support SI units. For the purposes of
this workshop, the subject model is in inches. The conversion based unit (#614316 in the file) should be used
by a STEP reader to convert the model on import. In this case, units of CM were chosen with a conversion factor
of 2.54 (again the STEP file includes this conversion constant). In the end, be sure to check that your final
size agrees with the numbers below (e.g., full-scale wing semi-span should be 1156.75 inches).
If possible, for consistency between grids,
it is recommended that the following geometry
definition for the freestream (farfield) boundary along with symmetry plane be used:
CRM-HL Boundary-Layer Tripping Information
from QinetiQ Test:
Geometric Reference Parameters for the NASA CRM-HL (full scale inches):
- Mean aerodynamic chord (MAC) = 275.8 in, located at y=468.75 in
- Wing semi-span (b/2) = 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
- Aspect Ratio (AR) = b2/Sref = 9.0
If you are generating your own meshes for the CRM-HL configuration instead of using the
provided baseline meshes,
you should try to follow the gridding guidelines found on the
Grids page, and the final grids must be made available to the HLPW Committee.
QinetiQ Wind Tunnel Geometry Files:
Not available yet; stay tuned. Note that the
CRM-HL model (given in full-scale inches) must be scaled to 10 percent size when run
in the QinetiQ tunnel. See the Test Case Document found on the
Test Cases Page.
Other Geometry Files:
Some of the TFGs are making use of other
geometries beside CRM-HL as part of their research for HLPW-4. These include:
- 2-D Multielement Airfoil based on CRM-HL
- NASA Juncture Flow Model F6-based wing and body with horn/leading edge
extension (Tests 640 and 653))
Please check periodically for updates, and/or get on the email distribution list by request to
to be notified directly of any updates/changes.
Link to: Grids Page
Link to: Test Cases Page
Return to: High Lift Prediction Workshop Home Page
Recent significant updates:
10/20/2020 - Added additional suggestions in red regarding problems/issues
10/13/2020 - Posted V2 geometry files and farfield/symmetry plane definition
09/25/2020 - Added tripping information from QinetiQ test
09/24/2020 - Added links to other geometry files
09/09/2020 - Updated note regarding STEP file details
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Last Updated: 10/22/2020