E201 (11.88%) (e201-il)
E201 (11.88%) - Eppler E201 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(e201-il) E201 (11.88%) Eppler E201 low Reynolds number airfoil Max thickness 11.9% at 30.8% chord. Max camber 2.6% at 49.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E201 (11.88%) 1.00000 0.00000 0.99653 0.00058 0.98650 0.00250 0.97069 0.00589 0.94977 0.01042 0.92406 0.01565 0.89369 0.02141 0.85899 0.02771 0.82048 0.03454 0.77871 0.04176 0.73427 0.04923 0.68777 0.05677 0.63984 0.06419 0.59110 0.07122 0.54222 0.07754 0.49365 0.08271 0.44572 0.08644 0.39870 0.08855 0.35285 0.08895 0.30843 0.08764 0.26565 0.08471 0.22484 0.08042 0.18642 0.07496 0.15078 0.06847 0.11828 0.06112 0.08925 0.05305 0.06396 0.04443 0.04264 0.03545 0.02547 0.02632 0.01258 0.01731 0.00407 0.00876 0.00011 0.00128 0.00187 -0.00488 0.00964 -0.01046 0.02258 -0.01574 0.04055 -0.02041 0.06341 -0.02437 0.09097 -0.02756 0.12298 -0.02993 0.15916 -0.03149 0.19915 -0.03227 0.24253 -0.03228 0.28883 -0.03157 0.33753 -0.03010 0.38823 -0.02776 0.44069 -0.02471 0.49439 -0.02131 0.54864 -0.01783 0.60272 -0.01444 0.65591 -0.01125 0.70749 -0.00839 0.75676 -0.00591 0.80305 -0.00386 0.84572 -0.00225 0.88416 -0.00107 0.91782 -0.00027 0.94625 0.00025 0.96912 0.00051 0.98602 0.00045 0.99646 0.00017 1.00000 0.00000 |
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Polars for E201 (11.88%) (e201-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e201-il | 50,000 | 9 | 34 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 50,000 | 5 | 33.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 100,000 | 9 | 56.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 100,000 | 5 | 57 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 200,000 | 9 | 80.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 200,000 | 5 | 78.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 500,000 | 9 | 112 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 500,000 | 5 | 104.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 1,000,000 | 9 | 135.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 1,000,000 | 5 | 122.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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