EPPLER 818 HYDROFOIL AIRFOIL (e818-il)
EPPLER 818 HYDROFOIL AIRFOIL - Eppler E818 hydrofoil
| Details | Dat file | Parser | |
|
(e818-il) EPPLER 818 HYDROFOIL AIRFOIL Eppler E818 hydrofoil Max thickness 9.4% at 33.1% chord. Max camber 2.8% at 67% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 818 HYDROFOIL AIRFOIL
35. 33.
0.0000100 -.0000300
0.0001700 0.0006600
0.0009600 0.0018600
0.0028000 0.0037000
0.0070900 0.0068200
0.0121100 0.0095500
0.0258700 0.0153900
0.0443800 0.0214800
0.0674700 0.0276200
0.0948500 0.0336700
0.1262600 0.0394700
0.1613700 0.0449200
0.1998300 0.0499000
0.2412400 0.0543300
0.2851700 0.0581200
0.3311700 0.0612200
0.3787700 0.0635500
0.4274600 0.0650800
0.4767600 0.0657500
0.5261500 0.0655700
0.5751100 0.0644800
0.6231300 0.0624900
0.6697200 0.0595500
0.7143500 0.0555800
0.7568300 0.0503300
0.7972500 0.0440100
0.8354000 0.0371800
0.8707400 0.0303400
0.9027100 0.0237600
0.9307801 0.0177000
0.9544200 0.0122300
0.9733900 0.0073400
0.9876500 0.0033300
0.9968000 0.0008100
1.0000000 0.0000000
0.0000100 -.0000300
0.0002000 -.0007100
0.0010400 -.0018700
0.0029500 -.0036300
0.0073500 -.0065500
0.0124800 -.0090600
0.0263300 -.0142400
0.0448000 -.0193900
0.0676500 -.0242700
0.0945600 -.0286600
0.1252300 -.0322800
0.1594300 -.0347900
0.1971400 -.0359900
0.2381800 -.0359900
0.2822600 -.0348300
0.3290100 -.0326100
0.3780600 -.0294400
0.4289800 -.0254900
0.4813000 -.0209300
0.5345100 -.0160200
0.5880300 -.0109800
0.6412400 -.0061000
0.6935100 -.0016300
0.7440900 0.0021900
0.7922200 0.0051500
0.8371300 0.0071000
0.8780300 0.0079600
0.9141600 0.0077300
0.9447800 0.0065100
0.9690900 0.0044800
0.9864200 0.0022600
0.9966400 0.0006000
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 818 HYDROFOIL AIRFOIL (e818-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e818-il | 50,000 | 9 | 23.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e818-il | 50,000 | 5 | 26.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e818-il | 100,000 | 9 | 66.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e818-il | 100,000 | 5 | 40.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e818-il | 200,000 | 9 | 56.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e818-il | 200,000 | 5 | 67.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e818-il | 500,000 | 9 | 104.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e818-il | 500,000 | 5 | 96.1 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e818-il | 1,000,000 | 9 | 126.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e818-il | 1,000,000 | 5 | 110.2 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||