E221 (9.39%) (e221-il)
E221 (9.39%) - Eppler E221 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(e221-il) E221 (9.39%) Eppler E221 low Reynolds number airfoil Max thickness 9.4% at 28.1% chord. Max camber 1.6% at 32.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E221 (9.39%) 1.00000 0.00000 0.99659 0.00010 0.98654 0.00064 0.97031 0.00191 0.94842 0.00392 0.92123 0.00654 0.88904 0.00975 0.85230 0.01365 0.81161 0.01826 0.76762 0.02349 0.72098 0.02922 0.67239 0.03526 0.62249 0.04137 0.57192 0.04726 0.52121 0.05263 0.47082 0.05725 0.42120 0.06094 0.37279 0.06356 0.32600 0.06499 0.28121 0.06514 0.23874 0.06397 0.19888 0.06153 0.16195 0.05790 0.12825 0.05319 0.09806 0.04752 0.07162 0.04101 0.04912 0.03384 0.03071 0.02621 0.01651 0.01835 0.00657 0.01059 0.00099 0.00344 0.00050 -0.00225 0.00577 -0.00702 0.01659 -0.01171 0.03256 -0.01597 0.05351 -0.01967 0.07930 -0.02272 0.10972 -0.02512 0.14450 -0.02688 0.18331 -0.02803 0.22575 -0.02863 0.27137 -0.02873 0.31968 -0.02840 0.37012 -0.02771 0.42212 -0.02670 0.47509 -0.02545 0.52841 -0.02399 0.58145 -0.02237 0.63360 -0.02062 0.68425 -0.01879 0.73281 -0.01689 0.77870 -0.01495 0.82140 -0.01300 0.86038 -0.01104 0.89520 -0.00908 0.92541 -0.00707 0.95082 -0.00490 0.97139 -0.00276 0.98687 -0.00110 0.99664 -0.00023 1.00000 0.00000 |
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Polars for E221 (9.39%) (e221-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e221-il | 50,000 | 9 | 29.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e221-il | 50,000 | 5 | 33.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e221-il | 100,000 | 9 | 47 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e221-il | 100,000 | 5 | 48.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e221-il | 200,000 | 9 | 64.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e221-il | 200,000 | 5 | 62.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e221-il | 500,000 | 9 | 86.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e221-il | 500,000 | 5 | 79.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e221-il | 1,000,000 | 9 | 100.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e221-il | 1,000,000 | 5 | 90.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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