E62 (5.62%) (e62-il)
E62 (5.62%) - Eppler E62 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(e62-il) E62 (5.62%) Eppler E62 low Reynolds number airfoil Max thickness 5.6% at 26.2% chord. Max camber 5% at 49.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E62 (5.62%) 1.00000 0.00000 0.99699 0.00098 0.98840 0.00397 0.97509 0.00876 0.95764 0.01463 0.93610 0.02086 0.91030 0.02718 0.88036 0.03363 0.84665 0.04017 0.80955 0.04667 0.76951 0.05301 0.72697 0.05905 0.68242 0.06463 0.63636 0.06957 0.58925 0.07364 0.54145 0.07669 0.49334 0.07861 0.44527 0.07939 0.39768 0.07909 0.35102 0.07778 0.30578 0.07547 0.26238 0.07222 0.22126 0.06806 0.18280 0.06308 0.14736 0.05734 0.11523 0.05094 0.08672 0.04401 0.06202 0.03667 0.04133 0.02910 0.02476 0.02148 0.01238 0.01408 0.00421 0.00720 0.00024 0.00140 0.00115 -0.00240 0.00762 -0.00447 0.01974 -0.00537 0.03744 -0.00502 0.06068 -0.00351 0.08936 -0.00098 0.12328 0.00236 0.16216 0.00630 0.20561 0.01060 0.25315 0.01501 0.30425 0.01928 0.35828 0.02314 0.41449 0.02626 0.47195 0.02854 0.52982 0.02996 0.58733 0.03056 0.64371 0.03032 0.69823 0.02929 0.75016 0.02750 0.79879 0.02504 0.84347 0.02198 0.88357 0.01847 0.91854 0.01462 0.94785 0.01059 0.97092 0.00656 0.98725 0.00308 0.99685 0.00078 1.00000 0.00000 |
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Polars for E62 (5.62%) (e62-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e62-il | 50,000 | 9 | 48 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 50,000 | 5 | 47.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 100,000 | 9 | 74.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 100,000 | 5 | 74.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 200,000 | 9 | 107.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 200,000 | 5 | 104.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 500,000 | 9 | 156.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 500,000 | 5 | 141.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 1,000,000 | 9 | 191.5 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 1,000,000 | 5 | 164.6 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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