E210 (13.64%) (e210-il)
E210 (13.64%) - Eppler E210 low Reynolds number airfoil
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(e210-il) E210 (13.64%) Eppler E210 low Reynolds number airfoil Max thickness 13.6% at 32.1% chord. Max camber 3.7% at 50.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E210 (13.64%) 1.00000 0.00000 0.99649 0.00099 0.98657 0.00414 0.97139 0.00936 0.95177 0.01587 0.92780 0.02285 0.89930 0.03003 0.86643 0.03752 0.82966 0.04531 0.78948 0.05329 0.74640 0.06133 0.70096 0.06928 0.65374 0.07698 0.60532 0.08427 0.55630 0.09093 0.50729 0.09677 0.45890 0.10148 0.41157 0.10470 0.36556 0.10619 0.32115 0.10583 0.27857 0.10360 0.23805 0.09952 0.19976 0.09375 0.16395 0.08656 0.13099 0.07822 0.10119 0.06893 0.07485 0.05890 0.05220 0.04836 0.03344 0.03755 0.01874 0.02675 0.00820 0.01630 0.00192 0.00664 0.00011 -0.00142 0.00415 -0.00786 0.01439 -0.01363 0.02986 -0.01884 0.05040 -0.02327 0.07585 -0.02686 0.10596 -0.02961 0.14043 -0.03150 0.17889 -0.03256 0.22092 -0.03282 0.26604 -0.03226 0.31370 -0.03090 0.36333 -0.02858 0.41467 -0.02499 0.46778 -0.02034 0.52228 -0.01529 0.57738 -0.01033 0.63227 -0.00574 0.68610 -0.00175 0.73807 0.00150 0.78735 0.00390 0.83317 0.00541 0.87478 0.00603 0.91146 0.00582 0.94253 0.00486 0.96733 0.00340 0.98536 0.00181 0.99632 0.00051 1.00000 0.00000 |
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Polars for E210 (13.64%) (e210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e210-il | 50,000 | 9 | 9.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 50,000 | 5 | 30.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 100,000 | 9 | 52.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 100,000 | 5 | 57.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 200,000 | 9 | 78.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 200,000 | 5 | 79.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 500,000 | 9 | 113 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 500,000 | 5 | 109 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 1,000,000 | 9 | 140.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 1,000,000 | 5 | 129.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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