EPPLER 547 AIRFOIL (e547-il)
EPPLER 547 AIRFOIL - Eppler E547 general aviation airfoil
| Details | Dat file | Parser | |
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(e547-il) EPPLER 547 AIRFOIL Eppler E547 general aviation airfoil Max thickness 17.4% at 40.3% chord. Max camber 2% at 30.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 547 AIRFOIL
35. 38.
0.0000200 0.0004500
0.0001700 0.0020500
0.0005400 0.0037400
0.0014500 0.0064400
0.0031100 0.0098800
0.0108000 0.0200700
0.0229100 0.0308900
0.0392900 0.0419100
0.0597900 0.0527700
0.0842300 0.0632000
0.1123700 0.0729700
0.1439700 0.0818600
0.1787200 0.0896800
0.2162700 0.0962700
0.2562500 0.1014500
0.2982500 0.1050000
0.3419200 0.1066700
0.3870900 0.1062600
0.4336400 0.1037700
0.4813800 0.0994400
0.5299000 0.0935300
0.5787900 0.0862900
0.6276000 0.0780200
0.6758300 0.0690200
0.7229500 0.0596300
0.7683800 0.0501900
0.8115200 0.0410300
0.8517000 0.0324600
0.8882599 0.0247200
0.9205300 0.0179600
0.9478500 0.0122900
0.9696300 0.0075700
0.9857500 0.0036000
0.9962200 0.0008900
1.0000000 0.0000000
0.0000200 0.0004500
0.0000200 -.0003000
0.0000900 -.0010200
0.0002400 -.0016900
0.0005000 -.0023300
0.0008500 -.0029800
0.0012900 -.0036500
0.0023800 -.0049900
0.0037300 -.0063600
0.0062200 -.0084500
0.0131900 -.0129900
0.0285200 -.0201400
0.0489900 -.0271200
0.0743000 -.0338200
0.1041600 -.0401200
0.1382100 -.0460100
0.1759900 -.0514400
0.2169900 -.0563200
0.2607100 -.0605500
0.3065900 -.0640200
0.3540800 -.0666000
0.4026200 -.0681800
0.4516200 -.0685800
0.5005100 -.0676400
0.5486700 -.0649200
0.5961000 -.0597700
0.6433700 -.0522000
0.6908500 -.0430100
0.7382400 -.0334200
0.7846000 -.0243600
0.8289200 -.0164200
0.8701300 -.0099800
0.9071600 -.0052200
0.9390100 -.0020700
0.9648600 -.0003100
0.9840600 0.0003300
0.9959600 0.0002000
1.0000000 0.0000000
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Polars for EPPLER 547 AIRFOIL (e547-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e547-il | 50,000 | 9 | 6.3 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 50,000 | 5 | 15 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 100,000 | 9 | 41.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 100,000 | 5 | 41 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 200,000 | 9 | 61.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 200,000 | 5 | 62 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 500,000 | 9 | 90.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 500,000 | 5 | 85.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 1,000,000 | 9 | 111.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 1,000,000 | 5 | 101.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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