EPPLER 585 AIRFOIL (e585-il)
EPPLER 585 AIRFOIL - Eppler E585 sailplane airfoil
| Details | Dat file | Parser | |
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(e585-il) EPPLER 585 AIRFOIL Eppler E585 sailplane airfoil Max thickness 14.6% at 37.6% chord. Max camber 4.2% at 42.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 585 AIRFOIL
35. 38.
0.0000100 0.0009500
0.0002100 0.0024800
0.0008500 0.0049600
0.0024100 0.0087000
0.0091600 0.0186000
0.0201200 0.0293700
0.0351900 0.0405400
0.0542800 0.0517300
0.0772500 0.0626300
0.1039400 0.0729800
0.1341500 0.0825800
0.1676100 0.0912400
0.2040400 0.0987900
0.2431200 0.1051000
0.2844700 0.1100600
0.3277200 0.1135500
0.3724400 0.1155000
0.4158000 0.1158000
0.4646400 0.1143600
0.5113800 0.1111100
0.5581300 0.1060500
0.6046000 0.0992500
0.6506000 0.0908400
0.6959700 0.0812000
0.7403200 0.0709000
0.7830500 0.0604200
0.8234600 0.0501200
0.8610100 0.0402700
0.8950599 0.0311100
0.9250500 0.0228400
0.9504500 0.0155500
0.9709300 0.0092100
0.9864399 0.0041600
0.9964600 0.0010200
1.0000000 0.0000000
0.0000100 0.0009500
0.0000100 -.0004700
0.0000800 -.0011200
0.0002100 -.0017300
0.0004100 -.0022900
0.0007100 -.0028100
0.0011200 -.0033200
0.0016100 -.0038300
0.0028000 -.0048500
0.0042700 -.0058600
0.0069400 -.0073600
0.0136000 -.0102100
0.0294800 -.0146600
0.0508200 -.0184700
0.0773800 -.0216600
0.1088800 -.0242600
0.1449500 -.0263600
0.1851000 -.0280300
0.2288300 -.0292700
0.2755800 -.0301200
0.3247700 -.0305800
0.3757700 -.0306400
0.4279400 -.0302600
0.4806300 -.0293900
0.5331800 -.0279300
0.5849300 -.0256400
0.6355800 -.0221300
0.6851600 -.0173800
0.7336500 -.0117600
0.7809300 -.0059700
0.8263000 -.0010100
0.8685800 0.0025400
0.9066200 0.0044900
0.9393600 0.0048500
0.9657200 0.0038500
0.9848000 0.0021500
0.9962200 0.0006100
1.0000000 0.0000000
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Polars for EPPLER 585 AIRFOIL (e585-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e585-il | 50,000 | 9 | 8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 50,000 | 5 | 21.2 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 100,000 | 9 | 50.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 100,000 | 5 | 47.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 200,000 | 9 | 81.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 200,000 | 5 | 78.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 500,000 | 9 | 118 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 500,000 | 5 | 110.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 1,000,000 | 9 | 146.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 1,000,000 | 5 | 131.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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