EPPLER 560 AIRFOIL (e560-il)
EPPLER 560 AIRFOIL - Eppler E560 general aviation airfoil
| Details | Dat file | Parser | |
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(e560-il) EPPLER 560 AIRFOIL Eppler E560 general aviation airfoil Max thickness 16.1% at 24% chord. Max camber 4.9% at 51.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 560 AIRFOIL
33. 29.
0.0000100 -.0000300
0.0028700 0.0103700
0.0100900 0.0222100
0.0214100 0.0347300
0.0367400 0.0474700
0.0559100 0.0600900
0.0787600 0.0722400
0.1050900 0.0836400
0.1346400 0.0939900
0.1671900 0.1030100
0.2024800 0.1104000
0.2403400 0.1159000
0.2806400 0.1193700
0.3232200 0.1207800
0.3678600 0.1202200
0.4142500 0.1178800
0.4619700 0.1139200
0.5105900 0.1085500
0.5596300 0.1019600
0.6085800 0.0943900
0.6569100 0.0860700
0.7040700 0.0772500
0.7494800 0.0681700
0.7925701 0.0590400
0.8327700 0.0500600
0.8695300 0.0414000
0.9023400 0.0332000
0.9307100 0.0255500
0.9541900 0.0184100
0.9727800 0.0115400
0.9869800 0.0054300
0.9965200 0.0013500
1.0000000 0.0000000
0.0000100 -.0000300
0.0029000 -.0089000
0.0118200 -.0172500
0.0255400 -.0253700
0.0437000 -.0327000
0.0661300 -.0389100
0.0926800 -.0437200
0.1231800 -.0469000
0.1575100 -.0482400
0.1955800 -.0476300
0.2373200 -.0450600
0.2826300 -.0406900
0.3313600 -.0347900
0.3832900 -.0278300
0.4379000 -.0204800
0.4943700 -.0132700
0.5518300 -.0065600
0.6093800 -.0006400
0.6661000 0.0042800
0.7210701 0.0080500
0.7733999 0.0105800
0.8222000 0.0118500
0.8666200 0.0118800
0.9058500 0.0107900
0.9391600 0.0087300
0.9657300 0.0059300
0.9848300 0.0030300
0.9962200 0.0008200
1.0000000 0.0000000
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Polars for EPPLER 560 AIRFOIL (e560-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e560-il | 50,000 | 9 | 7.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e560-il | 50,000 | 5 | 31.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e560-il | 100,000 | 9 | 45.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e560-il | 100,000 | 5 | 54.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e560-il | 200,000 | 9 | 72.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e560-il | 200,000 | 5 | 75.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e560-il | 500,000 | 9 | 105.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e560-il | 500,000 | 5 | 103.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e560-il | 1,000,000 | 9 | 133.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e560-il | 1,000,000 | 5 | 123.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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