EPPLER 908 AIRFOIL (e908-il)
EPPLER 908 AIRFOIL - Eppler E908 hydrofoil
| Details | Dat file | Parser | |
|
(e908-il) EPPLER 908 AIRFOIL Eppler E908 hydrofoil Max thickness 9% at 44.8% chord. Max camber 2.8% at 66.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 908 AIRFOIL
57.0 53.0
0.0000200 0.0002300
0.0013500 0.0022400
0.0044000 0.0047600
0.0090500 0.0075800
0.0152400 0.0106200
0.0229500 0.0138100
0.0321400 0.0171300
0.0427900 0.0205200
0.0548500 0.0239600
0.0682900 0.0274300
0.0830600 0.0308900
0.0991200 0.0343400
0.1164200 0.0377600
0.1348800 0.0411400
0.1544200 0.0444400
0.1750000 0.0476200
0.1965300 0.0506700
0.2189700 0.0535700
0.2422300 0.0562900
0.2662500 0.0588300
0.2909500 0.0611800
0.3162200 0.0633200
0.3419900 0.0652100
0.3681900 0.0668400
0.3947300 0.0681900
0.4215200 0.0692500
0.4484900 0.0700000
0.4755400 0.0704000
0.5026400 0.0704100
0.5297700 0.0700700
0.5568400 0.0694100
0.5837600 0.0684600
0.6104400 0.0672300
0.6367800 0.0657300
0.6627100 0.0639800
0.6881300 0.0619800
0.7129500 0.0597300
0.7371000 0.0572600
0.7604900 0.0545500
0.7830300 0.0516100
0.8046400 0.0484200
0.8252900 0.0448800
0.8450900 0.0409700
0.8641200 0.0368800
0.8822700 0.0327800
0.8994200 0.0287400
0.9154600 0.0248400
0.9302900 0.0210900
0.9438100 0.0175500
0.9559200 0.0141800
0.9665800 0.0109200
0.9759200 0.0078100
0.9839500 0.0050100
0.9906000 0.0027300
0.9956700 0.0011200
0.9988900 0.0002500
1.0000000 0.0000000
0.0000200 0.0002300
0.0008300 -.0015400
0.0037500 -.0035500
0.0083200 -.0057100
0.0145000 -.0079300
0.0222200 -.0101400
0.0314400 -.0123000
0.0421300 -.0143700
0.0542200 -.0163000
0.0676800 -.0180300
0.0824900 -.0194400
0.0987600 -.0205100
0.1165100 -.0213300
0.1356500 -.0219700
0.1561200 -.0224600
0.1778300 -.0228000
0.2006900 -.0230200
0.2246200 -.0231200
0.2495300 -.0231100
0.2753200 -.0230000
0.3019000 -.0227800
0.3291600 -.0224700
0.3570000 -.0220600
0.3853300 -.0215400
0.4140300 -.0209300
0.4429900 -.0202000
0.4721200 -.0193600
0.5013000 -.0183800
0.5304100 -.0172400
0.5593400 -.0158800
0.5881000 -.0141400
0.6168300 -.0120900
0.6455100 -.0099300
0.6739800 -.0078000
0.7020900 -.0057700
0.7297000 -.0039000
0.7566500 -.0023300
0.7828100 -.0007700
0.8080400 0.0004500
0.8321900 0.0014200
0.8551400 0.0021400
0.8767600 0.0026300
0.8969300 0.0028900
0.9155500 0.0029500
0.9325100 0.0028400
0.9477100 0.0026000
0.9611000 0.0022900
0.9726500 0.0019300
0.9822900 0.0015100
0.9899300 0.0010400
0.9954900 0.0005600
0.9988700 0.0001700
1.0000000 0.0000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for EPPLER 908 AIRFOIL (e908-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e908-il | 50,000 | 9 | 22.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e908-il | 50,000 | 5 | 24.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e908-il | 100,000 | 9 | 32.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e908-il | 100,000 | 5 | 41.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e908-il | 200,000 | 9 | 47.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e908-il | 200,000 | 5 | 62.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e908-il | 500,000 | 9 | 107.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e908-il | 500,000 | 5 | 91.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e908-il | 1,000,000 | 9 | 137 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e908-il | 1,000,000 | 5 | 117.9 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||