EPPLER 598 AIRFOIL (e598-il)
EPPLER 598 AIRFOIL - Eppler E598 airfoil
| Details | Dat file | Parser | |
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(e598-il) EPPLER 598 AIRFOIL Eppler E598 airfoil Max thickness 11.1% at 24.2% chord. Max camber 4.5% at 34.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 598 AIRFOIL
34. 38.
0.0000100 0.0001000
0.0001000 0.0016400
0.0006300 0.0043600
0.0049000 0.0136000
0.0131900 0.0238600
0.0254100 0.0346000
0.0414900 0.0454300
0.0613000 0.0560100
0.0847000 0.0660500
0.1114800 0.0752900
0.1413900 0.0834600
0.1742200 0.0902800
0.2097300 0.0955200
0.2477100 0.0989900
0.2879100 0.1005300
0.3301200 0.1000200
0.3741600 0.0973800
0.4198800 0.0926000
0.4672800 0.0858500
0.5162000 0.0776900
0.5661300 0.0686600
0.6164500 0.0592000
0.6665200 0.0497100
0.7156200 0.0405700
0.7630100 0.0320600
0.8079100 0.0244500
0.8495600 0.0178900
0.8872400 0.0124600
0.9202600 0.0081300
0.9480900 0.0048000
0.9703500 0.0023800
0.9866700 0.0008800
0.9966400 0.0001800
1.0000000 0.0000000
0.0000100 0.0001000
0.0000800 -.0013300
0.0001900 -.0020000
0.0003500 -.0026300
0.0005800 -.0032100
0.0009000 -.0037500
0.0013100 -.0042900
0.0017900 -.0048300
0.0029500 -.0058900
0.0043500 -.0069400
0.0068600 -.0084800
0.0181400 -.0129700
0.0347300 -.0164100
0.0564800 -.0184000
0.0835000 -.0189500
0.1158600 -.0182500
0.1533900 -.0167500
0.1955900 -.0148200
0.2419200 -.0126800
0.2917800 -.0106200
0.3444000 -.0089400
0.3987900 -.0077000
0.4541600 -.0067300
0.5098400 -.0059400
0.5652100 -.0052700
0.6196200 -.0047100
0.6724300 -.0042300
0.7230400 -.0038200
0.7708600 -.0034500
0.8153300 -.0031200
0.8559300 -.0028000
0.8921700 -.0024500
0.9236400 -.0020100
0.9500500 -.0014100
0.9712500 -.0007300
0.9869500 -.0002200
0.9966900 0.0000200
1.0000000 0.0000000
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Polars for EPPLER 598 AIRFOIL (e598-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e598-il | 50,000 | 9 | 9.9 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 50,000 | 5 | 23.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 100,000 | 9 | 43.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 100,000 | 5 | 50.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 200,000 | 9 | 72.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 200,000 | 5 | 75.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 500,000 | 9 | 109.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 500,000 | 5 | 106.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 1,000,000 | 9 | 137.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 1,000,000 | 5 | 128.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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