EPPLER 582 AIRFOIL (e582-il)
EPPLER 582 AIRFOIL - Eppler E582 sailplane airfoil
| Details | Dat file | Parser | |
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(e582-il) EPPLER 582 AIRFOIL Eppler E582 sailplane airfoil Max thickness 14.7% at 37.8% chord. Max camber 4.2% at 43.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 582 AIRFOIL
35. 38.
0.0000100 0.0008600
0.0002100 0.0023900
0.0008400 0.0048800
0.0023600 0.0086000
0.0090700 0.0185300
0.0200000 0.0293400
0.0350400 0.0405600
0.0541100 0.0518000
0.0770600 0.0627600
0.1037400 0.0731800
0.1339300 0.0828400
0.1673900 0.0915600
0.2038200 0.0991700
0.2429000 0.1055400
0.2842600 0.1105600
0.3275200 0.1141000
0.3722500 0.1161000
0.4180500 0.1164400
0.4644800 0.1150400
0.5112400 0.1118200
0.5579900 0.1067800
0.6044900 0.1000000
0.6505001 0.0916000
0.6955800 0.0819500
0.7402400 0.0716300
0.7829600 0.0611400
0.8234000 0.0507900
0.8609400 0.0409000
0.8949900 0.0316800
0.9249700 0.0233400
0.9503400 0.0159500
0.9708200 0.0094900
0.9863500 0.0042900
0.9964300 0.0010500
1.0000000 0.0000000
0.0000100 0.0008600
0.0000100 -.0005600
0.0000800 -.0012100
0.0002100 -.0018300
0.0004200 -.0023800
0.0007300 -.0029000
0.0011300 -.0034200
0.0016300 -.0039300
0.0028300 -.0049400
0.0043100 -.0059500
0.0069900 -.0074400
0.0137400 -.0103000
0.0297400 -.0147300
0.0512200 -.0185100
0.0779500 -.0216700
0.1096500 -.0242500
0.1459400 -.0263500
0.1863400 -.0280300
0.2303300 -.0293200
0.2773700 -.0302400
0.3268600 -.0308200
0.3781700 -.0310500
0.4306700 -.0309100
0.4836900 -.0303600
0.5365700 -.0293500
0.5886600 -.0277800
0.6393100 -.0255200
0.6878501 -.0221100
0.7345099 -.0168400
0.7802700 -.0102900
0.8248400 -.0041600
0.8669100 0.0005400
0.9051400 0.0034500
0.9383000 0.0044500
0.9651300 0.0037800
0.9845600 0.0021700
0.9961600 0.0006200
1.0000000 0.0000000
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Polars for EPPLER 582 AIRFOIL (e582-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e582-il | 50,000 | 9 | 7.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e582-il | 50,000 | 5 | 20.7 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e582-il | 100,000 | 9 | 47.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e582-il | 100,000 | 5 | 45.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e582-il | 200,000 | 9 | 78 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e582-il | 200,000 | 5 | 75 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e582-il | 500,000 | 9 | 112 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e582-il | 500,000 | 5 | 106.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e582-il | 1,000,000 | 9 | 140.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e582-il | 1,000,000 | 5 | 128.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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