EPPLER 417 AIRFOIL (e417-il)
EPPLER 417 AIRFOIL - Eppler E417 general purpose airfoil
| Details | Dat file | Parser | |
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(e417-il) EPPLER 417 AIRFOIL Eppler E417 general purpose airfoil Max thickness 14.2% at 38.3% chord. Max camber 3.1% at 76.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 417 AIRFOIL
32. 30.
0.0004300 0.0025200
0.0057100 0.0100700
0.0157200 0.0185100
0.0303200 0.0272700
0.0493700 0.0360200
0.0727400 0.0445300
0.1002300 0.0526100
0.1316200 0.0600900
0.1666300 0.0668600
0.2049400 0.0728000
0.2461800 0.0778400
0.2899500 0.0819700
0.3358200 0.0849900
0.3833400 0.0870200
0.4320200 0.0879900
0.4813500 0.0879200
0.5308400 0.0868000
0.5799600 0.0846600
0.6282000 0.0815400
0.6750400 0.0774800
0.7199700 0.0724800
0.7625700 0.0665300
0.8025100 0.0596900
0.8395000 0.0520200
0.8733500 0.0437300
0.9038700 0.0350700
0.9308800 0.0265100
0.9539100 0.0185200
0.9726200 0.0112500
0.9870000 0.0051700
0.9965600 0.0012800
1.0000000 0.0000000
0.0004300 0.0025200
0.0011700 -.0037800
0.0083200 -.0097700
0.0209000 -.0160500
0.0385500 -.0222900
0.0610000 -.0283100
0.0879800 -.0339700
0.1191600 -.0392000
0.1541300 -.0439000
0.1924600 -.0479700
0.2336900 -.0512700
0.2773200 -.0537000
0.3228400 -.0551000
0.3696800 -.0552600
0.4174500 -.0538700
0.4658300 -.0506900
0.5147200 -.0455300
0.5641400 -.0384100
0.6141700 -.0295900
0.6650200 -.0198100
0.7162600 -.0103400
0.7668000 -.0021800
0.8154000 0.0040700
0.8607800 0.0080600
0.9016500 0.0097100
0.9367900 0.0091100
0.9648600 0.0066400
0.9847200 0.0034300
0.9962600 0.0009200
1.0000000 0.0000000
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Polars for EPPLER 417 AIRFOIL (e417-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e417-il | 50,000 | 9 | 33.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e417-il | 50,000 | 5 | 30.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e417-il | 100,000 | 9 | 46.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e417-il | 100,000 | 5 | 46 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e417-il | 200,000 | 9 | 65.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e417-il | 200,000 | 5 | 66.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e417-il | 500,000 | 9 | 103.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e417-il | 500,000 | 5 | 94.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e417-il | 1,000,000 | 9 | 135.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e417-il | 1,000,000 | 5 | 112.5 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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