EPPLER 559 AIRFOIL (e559-il)
EPPLER 559 AIRFOIL - Eppler E559 general aviation airfoil
| Details | Dat file | Parser | |
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(e559-il) EPPLER 559 AIRFOIL Eppler E559 general aviation airfoil Max thickness 16% at 27.2% chord. Max camber 4.3% at 50.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 559 AIRFOIL
33. 29.
0.0001500 -.0020700
0.0017900 0.0075900
0.0080100 0.0189300
0.0184200 0.0310500
0.0328800 0.0434700
0.0512500 0.0558100
0.0733500 0.0677400
0.0989700 0.0789500
0.1278900 0.0891400
0.1598800 0.0980300
0.1946800 0.1053300
0.2321200 0.1107400
0.2721100 0.1141400
0.3144800 0.1155000
0.3590200 0.1149200
0.4054100 0.1125800
0.4532500 0.1086500
0.5020900 0.1033300
0.5514600 0.0968300
0.6008500 0.0893900
0.6497200 0.0812600
0.6975000 0.0726700
0.7436000 0.0638700
0.7874300 0.0550700
0.8284100 0.0464800
0.8659600 0.0382600
0.8995400 0.0305300
0.9286600 0.0233800
0.9528300 0.0167500
0.9720400 0.0104200
0.9866900 0.0048500
0.9964600 0.0011900
1.0000000 0.0000000
0.0001500 -.0020700
0.0044700 -.0104800
0.0147600 -.0188200
0.0297600 -.0269200
0.0491600 -.0342700
0.0727700 -.0405600
0.1004200 -.0455200
0.1319200 -.0489300
0.1671300 -.0505700
0.2059400 -.0503300
0.2482400 -.0482000
0.2939200 -.0443300
0.3428000 -.0389600
0.3946200 -.0325300
0.4488900 -.0256600
0.5047800 -.0188400
0.5614500 -.0124000
0.6180500 -.0066000
0.6737000 -.0016400
0.7275100 0.0023300
0.7786400 0.0052200
0.8262500 0.0070100
0.8695300 0.0077100
0.9077300 0.0074000
0.9401500 0.0062200
0.9660700 0.0043700
0.9848700 0.0023100
0.9962100 0.0006500
1.0000000 0.0000000
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Polars for EPPLER 559 AIRFOIL (e559-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e559-il | 50,000 | 9 | 8.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 50,000 | 5 | 30.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 100,000 | 9 | 43.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 100,000 | 5 | 52.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 200,000 | 9 | 70.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 200,000 | 5 | 73.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 500,000 | 9 | 103.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 500,000 | 5 | 101.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 1,000,000 | 9 | 130.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 1,000,000 | 5 | 123.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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