EPPLER 584 AIRFOIL (e584-il)
EPPLER 584 AIRFOIL - Eppler E584 sailplane airfoil
| Details | Dat file | Parser | |
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(e584-il) EPPLER 584 AIRFOIL Eppler E584 sailplane airfoil Max thickness 16.6% at 38.3% chord. Max camber 4.5% at 38.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 584 AIRFOIL
35. 38.
0.0000100 0.0002000
0.0001200 0.0018800
0.0006500 0.0045900
0.0021600 0.0089600
0.0086600 0.0198100
0.0193500 0.0316300
0.0341300 0.0439100
0.0528700 0.0562600
0.0754500 0.0683600
0.1016600 0.0799300
0.1313000 0.0907100
0.1641000 0.1004800
0.1997900 0.1090400
0.2380300 0.1162200
0.2784900 0.1218900
0.3207500 0.1258700
0.3644600 0.1280200
0.4092600 0.1282200
0.4547800 0.1264100
0.5006200 0.1224400
0.5466300 0.1160800
0.5930100 0.1075000
0.6396700 0.0962700
0.6860501 0.0863900
0.7315500 0.0749600
0.7755200 0.0635300
0.8172800 0.0524600
0.8561500 0.0420700
0.8914200 0.0325700
0.9224401 0.0241200
0.9485600 0.0166800
0.9695600 0.0100300
0.9856000 0.0045200
0.9962000 0.0010800
1.0000000 0.0000000
0.0000100 0.0002000
0.0000700 -.0013500
0.0001900 -.0020700
0.0003600 -.0027500
0.0006000 -.0033700
0.0009500 -.0039500
0.0014000 -.0045200
0.0019300 -.0050900
0.0032300 -.0062200
0.0048100 -.0073400
0.0076400 -.0090100
0.0143000 -.0120300
0.0307200 -.0170200
0.0526800 -.0213800
0.0799000 -.0251000
0.1120900 -.0282200
0.1488700 -.0308500
0.1897400 -.0330200
0.2341800 -.0347800
0.2816400 -.0361600
0.3314900 -.0371600
0.3831200 -.0377700
0.4358800 -.0379700
0.4891100 -.0377300
0.5421600 -.0370300
0.5943800 -.0357800
0.6451100 -.0339000
0.6937300 -.0312500
0.7395800 -.0273900
0.7829200 -.0215500
0.8248300 -.0142900
0.8652000 -.0073900
0.9027400 -.0020600
0.9360200 0.0011700
0.9631500 0.0021900
0.9837300 0.0016000
0.9959400 0.0005100
1.0000000 0.0000000
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Polars for EPPLER 584 AIRFOIL (e584-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e584-il | 50,000 | 9 | 4.5 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e584-il | 50,000 | 5 | 11.9 at α=-1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e584-il | 100,000 | 9 | 29.9 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e584-il | 100,000 | 5 | 32.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e584-il | 200,000 | 9 | 67.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e584-il | 200,000 | 5 | 64.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e584-il | 500,000 | 9 | 103.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e584-il | 500,000 | 5 | 101.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e584-il | 1,000,000 | 9 | 134 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e584-il | 1,000,000 | 5 | 126.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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