EPPLER 863 STRUT AIRFOIL (e863-il)
EPPLER 863 STRUT AIRFOIL - Eppler E863 strut airfoil
| Details | Dat file | Parser | |
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(e863-il) EPPLER 863 STRUT AIRFOIL Eppler E863 strut airfoil Max thickness 35.7% 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 863 STRUT AIRFOIL
31. 31.
0.0000000 0.0000000
0.0027500 0.0199600
0.0104800 0.0405500
0.0225100 0.0611400
0.0385800 0.0812100
0.0584800 0.1003400
0.0820100 0.1181200
0.1089300 0.1342200
0.1390100 0.1483100
0.1719700 0.1601000
0.2075000 0.1693000
0.2452800 0.1756000
0.2851000 0.1786500
0.3268000 0.1781800
0.3704400 0.1738700
0.4165000 0.1659100
0.4650200 0.1551600
0.5154900 0.1424300
0.5672800 0.1283500
0.6196700 0.1135100
0.6718600 0.0984800
0.7229600 0.0837300
0.7761600 0.0686200
0.8252400 0.0548900
0.8694200 0.0426700
0.9080300 0.0320700
0.9404600 0.0232200
0.9662100 0.0162000
0.9848900 0.0111100
0.9962100 0.0080300
1.0000000 0.0070000
0.0000000 0.0000000
0.0027500 -.0199600
0.0104800 -.0405500
0.0225100 -.0611400
0.0385800 -.0812100
0.0584800 -.1003400
0.0820100 -.1181200
0.1089300 -.1342200
0.1390100 -.1483100
0.1719700 -.1601000
0.2075000 -.1693000
0.2452800 -.1756000
0.2851000 -.1786500
0.3268000 -.1781800
0.3704400 -.1738700
0.4165000 -.1659100
0.4650200 -.1551600
0.5154900 -.1424300
0.5672800 -.1283500
0.6196700 -.1135100
0.6718600 -.0984800
0.7229600 -.0837300
0.7761600 -.0686200
0.8252400 -.0548900
0.8694200 -.0426700
0.9080300 -.0320700
0.9404600 -.0232200
0.9662100 -.0162000
0.9848900 -.0111100
0.9962100 -.0080300
1.0000000 -.0070000
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Polars for EPPLER 863 STRUT AIRFOIL (e863-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e863-il | 50,000 | 9 | 2.5 at α=-7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e863-il | 50,000 | 5 | 3.6 at α=-2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e863-il | 100,000 | 9 | 4.5 at α=-2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e863-il | 100,000 | 5 | 4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e863-il | 200,000 | 9 | 8.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e863-il | 200,000 | 5 | 24 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e863-il | 500,000 | 9 | 48.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e863-il | 500,000 | 5 | 44 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e863-il | 1,000,000 | 9 | 64.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e863-il | 1,000,000 | 5 | 62 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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