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TEST CASES

1st AIAA CFD High Lift Prediction Workshop


Image of an unstructured trap wing grid Image of a trap wing CFD solution

 

The Official Test Cases for HiLiftPW-1 are defined below. Please check periodically for updates, and/or register with hiliftpw@gmail.com to be notified directly of any changes.


 

For the required test cases, participants are asked to run on at least one supplied series of grids (if possible).


 

Case 1 (REQUIRED) - Grid Convergence Study

Trap Wing "Config 1" - Slat 30, Flap 25 (full span)

Flow solutions on a series of increasingly refined grids are required to assess grid convergence. If desired, participants can also run on independently-generated grids (built to specifications described in the Gridding Guidelines found on the Grids Page). Flow solutions on the coarse, medium, and fine mesh are required. An additional extra-fine mesh flow solution is optional.

Mach = 0.2
Angles-of-attack to be computed (deg) = 13 and 28
Reynolds number = 4.3 million based on mean aerodynamic chord (MAC)
Reference Temperature = 520 R


 

Case 2 (REQUIRED) - Flap Deflection Prediction Study

Medium Mesh from Grid Convergence Study

Mach = 0.2
Angles-of-attack to be computed (deg) = 6, 13, 21, 28, 32, 34, and 37
Reynolds number = 4.3 million based on MAC
Reference Temperature = 520 R


 

Case 3 (OPTIONAL) - Flap and Slat Support Effects Study

Trap Wing "Config 1" - Slat 30, Flap 25 with flap and slat bracket geometry modeled (nominally using medium mesh grid system)

Mach = 0.2
Angles-of-attack to be computed (deg) = 13 and 28
Reynolds number = 4.3 million based on MAC
Reference Temperature = 520 R


 

NOTES:


 

The above summary of test cases is also available for download as a PDF file: OfficialTestCases-HiLiftPW1-12August09.pdf

Although this results for this workshop are to be modeled as fully turbulent, information on transition from the experiment can be found in: McGinley et al, AIAA Paper 2005-5148, June 2005.


 

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Christopher Rumsey  

Last Updated
July 28, 2011

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