E203 (13.64%) (e203-il)
E203 (13.64%) - Eppler E203 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(e203-il) E203 (13.64%) Eppler E203 low Reynolds number airfoil Max thickness 13.6% at 30.7% chord. Max camber 2.3% at 54.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E203 (13.64%) 1.00000 0.00000 0.99645 0.00066 0.98625 0.00282 0.97030 0.00660 0.94932 0.01158 0.92361 0.01723 0.89325 0.02333 0.85854 0.02995 0.82000 0.03705 0.77819 0.04450 0.73369 0.05217 0.68712 0.05988 0.63910 0.06741 0.59028 0.07452 0.54130 0.08087 0.49264 0.08604 0.44460 0.08973 0.39748 0.09175 0.35154 0.09203 0.30704 0.09055 0.26419 0.08742 0.22332 0.08289 0.18486 0.07717 0.14920 0.07039 0.11671 0.06271 0.08772 0.05430 0.06250 0.04532 0.04128 0.03597 0.02427 0.02648 0.01161 0.01710 0.00344 0.00823 0.00002 0.00051 0.00258 -0.00625 0.01115 -0.01296 0.02471 -0.01953 0.04311 -0.02564 0.06616 -0.03113 0.09366 -0.03588 0.12534 -0.03979 0.16091 -0.04281 0.19999 -0.04489 0.24219 -0.04597 0.28702 -0.04602 0.33398 -0.04483 0.38286 -0.04210 0.43379 -0.03799 0.48643 -0.03314 0.54007 -0.02801 0.59395 -0.02289 0.64730 -0.01799 0.69937 -0.01350 0.74940 -0.00954 0.79665 -0.00620 0.84043 -0.00353 0.88005 -0.00156 0.91489 -0.00024 0.94441 0.00051 0.96813 0.00076 0.98561 0.00060 0.99636 0.00021 1.00000 0.00000 |
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Polars for E203 (13.64%) (e203-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e203-il | 50,000 | 9 | 32 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e203-il | 50,000 | 5 | 31.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e203-il | 100,000 | 9 | 54.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e203-il | 100,000 | 5 | 55 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e203-il | 200,000 | 9 | 78.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e203-il | 200,000 | 5 | 75.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e203-il | 500,000 | 9 | 109.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e203-il | 500,000 | 5 | 101.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e203-il | 1,000,000 | 9 | 132.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e203-il | 1,000,000 | 5 | 108.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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