As a result, for HLPW-5 there are multiple geometries being used. *These geometries are different in their
details from the geometry used in HLPW-4.* They are presented here for each of
the three HLPW-5 Test Cases. All are provided in full-scale inches.

- CRMHL_ReferenceSolid_WingBody_09222022.stp.zip
- The above CAD includes the farfield definition, which (for Case 1) should be a rectangular cuboid with dimensions -65000 ≤ x ≤ 65000 inches, 0 ≤ y ≤ 65000 inches, -65000 ≤ z ≤ 65000 inches.

- CRMHL_WB_09222022_NoDomain.zip
- With this CAD file, you must create the farfield boundary yourself (according to the above)

### Geometry files for the 4 configurations are available at: https://commonresearchmodel.larc.nasa.gov/high-lift-prediction-workshop-5-cad-files/

### Note that the geometries for test cases 2.2 and 2.3 were updated to Version 2 on 10/04/2023. A surface on the main element leading edge inadvertently had a fold where two surfaces connected. Many grid generators were able to grid over the fold with no consequence. In those cases the existing grids are considered to be valid, and there is no need to update the geometry.

### Farfield Definition: Farfield domain is preferred to be a hemisphere with distance 100*MAC, although other similar "best practice" domain extents are allowed.

### This test case uses the NASA 5.2% configuration, available at: https://commonresearchmodel.larc.nasa.gov/high-lift-crm/high-lift-crm-geometry/model-specific-geometry/ (labeled NASA5p2_CRMHL_LDG_V02)

### Farfield Definition: Farfield domain is preferred to be a hemisphere with distance 100*MAC, although other similar "best practice" domain extents are allowed.

__Note that these reference parameters remain the same across all test cases__

- Mean aerodynamic chord (MAC) = 275.8 in, located at y=468.75 in
- Use the MAC as the length scale in the definition of Reynolds number (Re)
- Use the MAC as the x-direction length to nondimensionalize pitching moment about the moment reference center (see Q12/A12 on the FAQs page)
- Reference area of the semi-span model = Sref/2 = 297,360.0 in
^{2} - Moment reference center (MRC): x=1325.90 in, y=0.0 in, z=177.95 in
- Note that the MRC is with respect to the particular coordinate system in which the geometry is provided (full-scale, in inches, with origin in front of and below the model nose). Y=0 is on the model's centerplane.
- Wing semi-span (b/2) = 1156.75 in
- Aspect Ratio (AR) = b
^{2}/Sref = 9.0 - In the wind tunnel, the standoff did not contribute to forces or moment

Link to: Grids Page

Link to: Test Cases Page

Return to: High Lift Prediction Workshop Home Page

Recent significant updates:

12/04/2023 - Added link to Case 3 geometry files

10/04/2023 - Note added regarding a minor geometry fix for Cases 2.2 and 2.3

05/25/2023 - Added link to Case 2 geometry files

04/24/2023 - Added CAD for Case 1 without farfield boundary definition included (some CAD readers have trouble with this)

**Responsible NASA Official:**
Christopher Rumsey

**Page Curator:**
Christopher Rumsey

**Last Updated:** 12/04/2023