EPPLER 67 AIRFOIL (e67-il)
EPPLER 67 AIRFOIL - Eppler E67 low Reynolds number airfoil
| Details | Dat file | Parser | |
|
(e67-il) EPPLER 67 AIRFOIL Eppler E67 low Reynolds number airfoil Max thickness 11.6% at 32.6% chord. Max camber 3.7% at 51.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 67 AIRFOIL
33. 30.
0.0000000 0.0000000
0.0008400 0.0036900
0.0063800 0.0118800
0.0163900 0.0208600
0.0307200 0.0301600
0.0493000 0.0394500
0.0719900 0.0484700
0.0986200 0.0570100
0.1289800 0.0649000
0.1627900 0.0719900
0.1997700 0.0781500
0.2395700 0.0832700
0.2818200 0.0872400
0.3261400 0.0899800
0.3721200 0.0914400
0.4193700 0.0915700
0.4674600 0.0903900
0.5159700 0.0879200
0.5644700 0.0842300
0.6125200 0.0794200
0.6596800 0.0736000
0.7055200 0.0669500
0.7495900 0.0596200
0.7914800 0.0518400
0.8307400 0.0438200
0.8669700 0.0358400
0.8997000 0.0281800
0.9284200 0.0210700
0.9526400 0.0146200
0.9721400 0.0088100
0.9869400 0.0040100
0.9965799 0.0009800
1.0000000 0.0000000
0.0000000 0.0000000
0.0006200 -.0029700
0.0062200 -.0087300
0.0171800 -.0143200
0.0331300 -.0192900
0.0539600 -.0234400
0.0795500 -.0266500
0.1097400 -.0288900
0.1442800 -.0301500
0.1829000 -.0304800
0.2252300 -.0299500
0.2708600 -.0286400
0.3193100 -.0266400
0.3700900 -.0240400
0.4226700 -.0209400
0.4764900 -.0175000
0.5309600 -.0138500
0.5854600 -.0101500
0.6393500 -.0065500
0.6919600 -.0032100
0.7426200 -.0002700
0.7906500 0.0021300
0.8353601 0.0038800
0.8760900 0.0049100
0.9121701 0.0051600
0.9429200 0.0046200
0.9676000 0.0033900
0.9855500 0.0018300
0.9963800 0.0005200
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 67 AIRFOIL (e67-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e67-il | 50,000 | 9 | 37.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 50,000 | 5 | 36.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 100,000 | 9 | 60.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 100,000 | 5 | 60.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 200,000 | 9 | 86.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 200,000 | 5 | 82.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 500,000 | 9 | 121.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 500,000 | 5 | 107.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 1,000,000 | 9 | 144.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 1,000,000 | 5 | 117.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||