File:A Boundary Layer Profile for Air Flow over a NACA0012 Wing.jpg
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Summary
| Description |
English: This figure shows the u(x,y) velocity profile on NACA0012 airfoil at x/c = 0.3 that was extracted from the simulation described in R. Swanson and S. Langer, NASA/TM-2016-219003. The u0 value is 0.5 M, the (3-sigma δi)/δ99 value is 311, and the umax value is 9% higher than the u0 value. |
| Date | |
| Source | Own work |
| Author | David Weyburne |
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| Date/Time | Thumbnail | Dimensions | User | Comment | |
|---|---|---|---|---|---|
| current | 10:54, 14 May 2020 | | 1,800 × 1,380 (288 KB) | David Weyburne | Uploaded own work with UploadWizard |
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