GEOMETRY FILES

5th AIAA CFD High Lift Prediction Workshop

The configuration used in HLPW-5 is again the NASA High-Lift Common Research Model (CRM-HL). A general description of the CRM-HL can be found in AIAA Paper 2020-2771 (Lacy & Clark). Now, with expanded testing in the CRM-HL "ecosystem," there are often different areas of emphasis each time an ecosystem partner conducts a wind tunnel test. It is also important to note that the support hardware - such as slat brackets and flap supports - sometimes require minor redesigns because of particular wind tunnel requirements.

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.

Note that the last 2 inches (full scale) of the original CRM-HL fuselage geometry was purposefully cut off in the CAD files, to avoid problematic curvature that could cause issues for some CFD methods. Thus, the CAD fuselage length is very slightly different from many of the built CRM-HL models. This very minor change has no effect on any of the results of interest.

Test Case 1: CRM-HL Wing-Body Verification

CRM-HL Wing-Body configuration (STP file):

• 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.

CRM-HL Wing-Body configuration without the farfield boundary definition (STP file):

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

 
 

Test Case 2: Configuration Buildup

• 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.

Test Case 3: Reynolds Number Study

• 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: STEP files only support SI units. However, the CAD files were created with the intention of the subject model being in inches. 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).

Geometric Reference Parameters for the NASA CRM-HL (full scale inches):

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 in²
• 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) = b²/Sref = 9.0
• In the wind tunnel, the standoff did not contribute to forces or moment

If you are generating your own 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.

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.

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)

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Responsible NASA Official: Christopher Rumsey
Page Curator: Christopher Rumsey
Last Updated: 12/04/2023