(Dicke 12.28%) (e171-il)
(Dicke 12.28%) - Eppler E171 low Reynolds number airfoil
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(e171-il) (Dicke 12.28%) Eppler E171 low Reynolds number airfoil Max thickness 12.3% at 32.4% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
(Dicke 12.28%) 1.00000 0.00000 0.99644 0.00023 0.98613 0.00120 0.96985 0.00302 0.94806 0.00536 0.92086 0.00808 0.88853 0.01134 0.85160 0.01525 0.81068 0.01980 0.76641 0.02493 0.71950 0.03052 0.67062 0.03638 0.62048 0.04228 0.56975 0.04795 0.51907 0.05302 0.46887 0.05707 0.41943 0.05984 0.37102 0.06123 0.32389 0.06127 0.27839 0.06013 0.23501 0.05796 0.19422 0.05482 0.15645 0.05078 0.12207 0.04593 0.09142 0.04034 0.06481 0.03412 0.04247 0.02739 0.02461 0.02033 0.01138 0.01314 0.00297 0.00613 0.00000 0.00000 0.00297 -0.00613 0.01138 -0.01314 0.02461 -0.02033 0.04247 -0.02739 0.06481 -0.03412 0.09142 -0.04034 0.12207 -0.04593 0.15645 -0.05078 0.19422 -0.05482 0.23501 -0.05796 0.27839 -0.06013 0.32389 -0.06127 0.37102 -0.06123 0.41943 -0.05984 0.46887 -0.05707 0.51907 -0.05302 0.56975 -0.04795 0.62048 -0.04228 0.67062 -0.03638 0.71950 -0.03052 0.76641 -0.02493 0.81068 -0.01980 0.85160 -0.01525 0.88853 -0.01134 0.92086 -0.00808 0.94806 -0.00536 0.96985 -0.00302 0.98613 -0.00120 0.99644 -0.00023 1.00000 0.00000 |
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Polars for (Dicke 12.28%) (e171-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e171-il | 50,000 | 9 | 29.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 50,000 | 5 | 29.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 100,000 | 9 | 43.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 100,000 | 5 | 41.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 200,000 | 9 | 56.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 200,000 | 5 | 47.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 500,000 | 9 | 65.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 500,000 | 5 | 56.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 1,000,000 | 9 | 68.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 1,000,000 | 5 | 68.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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