EPPLER 580 AIRFOIL (e580-il)
EPPLER 580 AIRFOIL - Eppler E580 general purpose airfoil
| Details | Dat file | Parser | |
|
(e580-il) EPPLER 580 AIRFOIL Eppler E580 general purpose airfoil Max thickness 16.1% at 33% chord. Max camber 4.1% at 61.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 580 AIRFOIL
33. 29.
0.0000100 -.0001000
0.0028200 0.0091500
0.0099700 0.0198600
0.0213200 0.0313000
0.0367600 0.0430300
0.0561800 0.0547000
0.0794300 0.0660000
0.1063300 0.0766800
0.1366500 0.0865000
0.1701000 0.0952400
0.2064400 0.1026900
0.2453600 0.1086700
0.2865700 0.1130400
0.3297700 0.1157200
0.3746100 0.1166600
0.4207200 0.1158300
0.4677800 0.1131900
0.5155500 0.1088500
0.5636800 0.1030800
0.6116700 0.0961500
0.6590000 0.0882900
0.7051700 0.0797100
0.7496499 0.0706700
0.7919100 0.0613800
0.8314400 0.0520700
0.8677000 0.0429500
0.9002100 0.0342100
0.9284500 0.0259000
0.9522100 0.0179400
0.9716600 0.0106100
0.9867000 0.0047400
0.9965300 0.0011500
1.0000000 0.0000000
0.0000100 -.0001000
0.0029400 -.0071900
0.0124300 -.0130600
0.0276900 -.0187100
0.0482800 -.0239500
0.0738300 -.0287200
0.1040300 -.0329900
0.1384400 -.0367500
0.1765500 -.0399500
0.2178200 -.0424900
0.2617100 -.0442300
0.3076300 -.0450100
0.3549900 -.0445200
0.4034300 -.0423300
0.4528400 -.0381500
0.5033400 -.0317700
0.5554200 -.0236300
0.6089300 -.0149100
0.6630200 -.0065900
0.7166700 0.0006700
0.7688000 0.0063700
0.8182600 0.0101900
0.8638800 0.0120000
0.9045400 0.0117800
0.9390000 0.0096800
0.9660400 0.0064300
0.9851100 0.0031700
0.9963200 0.0008400
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 580 AIRFOIL (e580-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e580-il | 50,000 | 9 | 7.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e580-il | 50,000 | 5 | 24.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e580-il | 100,000 | 9 | 52.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e580-il | 100,000 | 5 | 54.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e580-il | 200,000 | 9 | 76.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e580-il | 200,000 | 5 | 76.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e580-il | 500,000 | 9 | 107.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e580-il | 500,000 | 5 | 102 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e580-il | 1,000,000 | 9 | 131.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e580-il | 1,000,000 | 5 | 120.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||