EPPLER 558 AIRFOIL (e558-il)
EPPLER 558 AIRFOIL - Eppler E558 general aviation airfoil
| Details | Dat file | Parser | |
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(e558-il) EPPLER 558 AIRFOIL Eppler E558 general aviation airfoil Max thickness 16% at 26.4% chord. Max camber 3.8% at 49.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 558 AIRFOIL
33. 29.
0.0007500 -.0043500
0.0007700 0.0046500
0.0060100 0.0155000
0.0155100 0.0272500
0.0291300 0.0393700
0.0466900 0.0514700
0.0680400 0.0632100
0.0929700 0.0742600
0.1212400 0.0843300
0.1526500 0.0931200
0.1869300 0.1003400
0.2239400 0.1056900
0.2635800 0.1090300
0.3057000 0.1103500
0.3500900 0.1097300
0.3964500 0.1073700
0.4443700 0.1034400
0.4934200 0.0981500
0.5431100 0.0917200
0.5929400 0.0843800
0.6423400 0.0764000
0.6907499 0.0680100
0.7375600 0.0594700
0.7821600 0.0510000
0.8239400 0.0427900
0.8623000 0.0350000
0.8966900 0.0277600
0.9265700 0.0211200
0.9514601 0.0150300
0.9712999 0.0092700
0.9864100 0.0042500
0.9964100 0.0010300
1.0000000 0.0000000
0.0007500 -.0043500
0.0068100 -.0124100
0.0183600 -.0207500
0.0345600 -.0288200
0.0551100 -.0362000
0.0798300 -.0425600
0.1085100 -.0476700
0.1409300 -.0513000
0.1769300 -.0532200
0.2164000 -.0533200
0.2591900 -.0515900
0.3051700 -.0481600
0.3541300 -.0432600
0.4058200 -.0372900
0.4597000 -.0308400
0.5150000 -.0243400
0.5709100 -.0181100
0.6265800 -.0123800
0.6811799 -.0073500
0.7338800 -.0031600
0.7838500 0.0001100
0.8303100 0.0024100
0.8724900 0.0037400
0.9096900 0.0041800
0.9412300 0.0038300
0.9665100 0.0028800
0.9749700 0.0016200
0.9962200 0.0004800
1.0000000 0.0000000
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Polars for EPPLER 558 AIRFOIL (e558-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e558-il | 50,000 | 9 | 9.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 50,000 | 5 | 29.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 100,000 | 9 | 41.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 100,000 | 5 | 50.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 200,000 | 9 | 67.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 200,000 | 5 | 70.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 500,000 | 9 | 100.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 500,000 | 5 | 99.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 1,000,000 | 9 | 127 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 1,000,000 | 5 | 120.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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