EPPLER 862 STRUT AIRFOIL (e862-il)
EPPLER 862 STRUT AIRFOIL - Eppler E862 strut airfoil
| Details | Dat file | Parser | |
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(e862-il) EPPLER 862 STRUT AIRFOIL Eppler E862 strut airfoil Max thickness 32.4% at 28.5% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 862 STRUT AIRFOIL
31. 31.
0.0000000 0.0000000
0.0027100 0.0184800
0.0103500 0.0375900
0.0222600 0.0566800
0.0381700 0.0752500
0.0579000 0.0928700
0.0812600 0.1091800
0.1080400 0.1238100
0.1380200 0.1364800
0.1709500 0.1468900
0.2065400 0.1548000
0.2445000 0.1599000
0.2846700 0.1618700
0.3269800 0.1605400
0.3714300 0.1558100
0.4182500 0.1479100
0.4673800 0.1375800
0.5182900 0.1255200
0.5703800 0.1123100
0.6229300 0.0985100
0.6751700 0.0846200
0.7262300 0.0711100
0.7787700 0.0577500
0.8272600 0.0459100
0.8709300 0.0355600
0.9091001 0.0267100
0.9411500 0.0193600
0.9666001 0.0135700
0.9850600 0.0093800
0.9962500 0.0068500
1.0000000 0.0060000
0.0000000 0.0000000
0.0027100 -.0184800
0.0103500 -.0375900
0.0222600 -.0566800
0.0381700 -.0752500
0.0579000 -.0928700
0.0812600 -.1091800
0.1080400 -.1238100
0.1380200 -.1364800
0.1709500 -.1468900
0.2065400 -.1548000
0.2445000 -.1599000
0.2846700 -.1618700
0.3269800 -.1605400
0.3714300 -.1558100
0.4182500 -.1479100
0.4673800 -.1375800
0.5182900 -.1255200
0.5703800 -.1123100
0.6229300 -.0985100
0.6751700 -.0846200
0.7262300 -.0711100
0.7787700 -.0577500
0.8272600 -.0459100
0.8709300 -.0355600
0.9091001 -.0267100
0.9411500 -.0193600
0.9666001 -.0135700
0.9850600 -.0093800
0.9962500 -.0068500
1.0000000 -.0060000
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Polars for EPPLER 862 STRUT AIRFOIL (e862-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e862-il | 50,000 | 9 | 2.8 at α=-4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 50,000 | 5 | 2.6 at α=-2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 100,000 | 9 | 5.1 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 100,000 | 5 | 10.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 200,000 | 9 | 20.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 200,000 | 5 | 32.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 500,000 | 9 | 57.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 500,000 | 5 | 54.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 1,000,000 | 9 | 78.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 1,000,000 | 5 | 74.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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