E214 (11.1%) (e214-il)
E214 (11.1%) - Eppler E214 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(e214-il) E214 (11.1%) Eppler E214 low Reynolds number airfoil Max thickness 11.1% at 33.1% chord. Max camber 3.7% at 56.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E214 (11.1%) 1.00000 0.00000 0.99669 0.00104 0.98737 0.00422 0.97312 0.00916 0.95431 0.01501 0.93081 0.02139 0.90279 0.02833 0.87072 0.03576 0.83508 0.04344 0.79626 0.05105 0.75457 0.05841 0.71040 0.06544 0.66430 0.07207 0.61682 0.07813 0.56852 0.08344 0.51991 0.08776 0.47142 0.09093 0.42346 0.09281 0.37645 0.09332 0.33076 0.09241 0.28674 0.09008 0.24474 0.08639 0.20510 0.08142 0.16816 0.07532 0.13424 0.06822 0.10365 0.06028 0.07665 0.05168 0.05349 0.04258 0.03434 0.03321 0.01934 0.02379 0.00856 0.01465 0.00210 0.00619 0.00005 -0.00086 0.00360 -0.00632 0.01326 -0.01087 0.02830 -0.01475 0.04858 -0.01784 0.07390 -0.02011 0.10406 -0.02161 0.13874 -0.02236 0.17759 -0.02245 0.22017 -0.02193 0.26599 -0.02086 0.31449 -0.01928 0.36508 -0.01721 0.41714 -0.01453 0.47030 -0.01100 0.52450 -0.00678 0.57932 -0.00245 0.63400 0.00155 0.68770 0.00495 0.73959 0.00756 0.78883 0.00923 0.83461 0.00994 0.87612 0.00970 0.91265 0.00862 0.94352 0.00684 0.96809 0.00461 0.98582 0.00235 0.99646 0.00065 1.00000 0.00000 |
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Polars for E214 (11.1%) (e214-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e214-il | 50,000 | 9 | 37.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e214-il | 50,000 | 5 | 39.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e214-il | 100,000 | 9 | 61.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e214-il | 100,000 | 5 | 63.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e214-il | 200,000 | 9 | 87.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e214-il | 200,000 | 5 | 84.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e214-il | 500,000 | 9 | 121.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e214-il | 500,000 | 5 | 111.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e214-il | 1,000,000 | 9 | 145.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e214-il | 1,000,000 | 5 | 122.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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