EPPLER 556 AIRFOIL (e556-il)
EPPLER 556 AIRFOIL - Eppler E556 general aviation airfoil
| Details | Dat file | Parser | |
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(e556-il) EPPLER 556 AIRFOIL Eppler E556 general aviation airfoil Max thickness 16% at 31.1% chord. Max camber 3.1% at 61.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 556 AIRFOIL
35. 38.
0.0000100 0.0004500
0.0001600 0.0021100
0.0005000 0.0038600
0.0013700 0.0066000
0.0058100 0.0145700
0.0153200 0.0250700
0.0291200 0.0358500
0.0471100 0.0465400
0.0691400 0.0568400
0.0950500 0.0665100
0.1246300 0.0753600
0.1576200 0.0831900
0.1937100 0.0898500
0.2325700 0.0951600
0.2739000 0.0989300
0.3174600 0.1010700
0.3629300 0.1016300
0.4099200 0.1006100
0.4580500 0.0980800
0.5069300 0.0941600
0.5561100 0.0889900
0.6051400 0.0827700
0.6535200 0.0756900
0.7007599 0.0679800
0.7463300 0.0599000
0.7896800 0.0516600
0.8302800 0.0435200
0.8675700 0.0356600
0.9010100 0.0282700
0.9301200 0.0214800
0.9544300 0.0154000
0.9735100 0.0099500
0.9874600 0.0049900
0.9966200 0.0013200
1.0000000 0.0000000
0.0000100 0.0004500
0.0000200 -.0003400
0.0000900 -.0011000
0.0002400 -.0018100
0.0004900 -.0025100
0.0008200 -.0032200
0.0012400 -.0039400
0.0022600 -.0053900
0.0035400 -.0068700
0.0058700 -.0091300
0.0075700 -.0105700
0.0197200 -.0182000
0.0368300 -.0256800
0.0586000 -.0328000
0.0847600 -.0394000
0.1149900 -.0453900
0.1488300 -.0506300
0.1858100 -.0549600
0.2254300 -.0581400
0.2671700 -.0597800
0.3108000 -.0593500
0.3564400 -.0565800
0.4041700 -.0515100
0.4541600 -.0444600
0.5062600 -.0362300
0.5598700 -.0275600
0.6142500 -.0190100
0.6685500 -.0111000
0.7218600 -.0042500
0.7731900 0.0011900
0.8215300 0.0050400
0.8658700 0.0072000
0.9052200 0.0077600
0.9386700 0.0069100
0.9653900 0.0050200
0.9846600 0.0026900
0.9961799 0.0007600
1.0000000 0.0000000
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Polars for EPPLER 556 AIRFOIL (e556-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e556-il | 50,000 | 9 | 25.5 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e556-il | 50,000 | 5 | 32.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e556-il | 100,000 | 9 | 52.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e556-il | 100,000 | 5 | 53.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e556-il | 200,000 | 9 | 72.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e556-il | 200,000 | 5 | 70.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e556-il | 500,000 | 9 | 97.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e556-il | 500,000 | 5 | 90.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e556-il | 1,000,000 | 9 | 116.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e556-il | 1,000,000 | 5 | 105.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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