Description: Pressure distribution and lift coefficient can be calculated by inputting NACA four-digit airfoil and environmental parameters.
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File list (Check if you may need any files):
| Filename | Size | Date |
|---|
| vortex cfd\foilcfdV2.m | 1607 | 2018-08-21
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| vortex cfd\foilchart.m | 62 | 2017-11-25
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| vortex cfd | 0 | 2018-11-27
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| vortex cfd\naca2507数据结果.fig | 23216 | 2017-11-25 |
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