EPPLER 557 AIRFOIL (e557-il)
EPPLER 557 AIRFOIL - Eppler E557 general aviation airfoil
| Details | Dat file | Parser | |
|
(e557-il) EPPLER 557 AIRFOIL Eppler E557 general aviation airfoil Max thickness 16% at 30.2% chord. Max camber 3.7% at 60.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 557 AIRFOIL
35. 37.
0.0000100 0.0003800
0.0001300 0.0020700
0.0004500 0.0038500
0.0015100 0.0072600
0.0074800 0.0174300
0.0178200 0.0283300
0.0323800 0.0394500
0.0510600 0.0504400
0.0737300 0.0610100
0.1002100 0.0709300
0.1302800 0.0799800
0.1636800 0.0879900
0.2001100 0.0948000
0.2392100 0.1002200
0.2806900 0.1040700
0.3243100 0.1062500
0.3697500 0.1067900
0.4166400 0.1057000
0.4646000 0.1030600
0.5132500 0.0989900
0.5621100 0.0936400
0.6107600 0.0871800
0.6587300 0.0798400
0.7054901 0.0718400
0.7505500 0.0634300
0.7933700 0.0548400
0.8334100 0.0463100
0.8701400 0.0380600
0.9030400 0.0302600
0.9316300 0.0230600
0.9554700 0.0165700
0.9741200 0.0107500
0.9877200 0.0054200
0.9966800 0.0014400
1.0000000 0.0000000
0.0000100 0.0003800
0.0000300 -.0004200
0.0001100 -.0011900
0.0002700 -.0019200
0.0005200 -.0026300
0.0008700 -.0033400
0.0012900 -.0040600
0.0023300 -.0055300
0.0036100 -.0070100
0.0059600 -.0092600
0.0163600 -.0162700
0.0323600 -.0235500
0.0531400 -.0304000
0.0784600 -.0366900
0.1079800 -.0423500
0.1412500 -.0472900
0.1777900 -.0513200
0.2170900 -.0542200
0.2586200 -.0556000
0.3021600 -.0549100
0.3478600 -.0518900
0.3958100 -.0466100
0.4461500 -.0394200
0.4987200 -.0311100
0.5529100 -.0224300
0.6079700 -.0139500
0.6630300 -.0061900
0.7171700 0.0003900
0.7693599 0.0054800
0.8185700 0.0088600
0.8637300 0.0104600
0.9038301 0.0103900
0.9379400 0.0088400
0.9651200 0.0062100
0.9846200 0.0032400
0.9961900 0.0009000
1.0000000 0.0000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for EPPLER 557 AIRFOIL (e557-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e557-il | 50,000 | 9 | 25.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 50,000 | 5 | 32.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 100,000 | 9 | 53.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 100,000 | 5 | 54.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 200,000 | 9 | 75 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 200,000 | 5 | 73.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 500,000 | 9 | 102.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 500,000 | 5 | 95.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 1,000,000 | 9 | 122.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 1,000,000 | 5 | 110.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||