EPPLER 664 AIRFOIL (e664-il)
EPPLER 664 AIRFOIL - Eppler E664 variable geometry sailplane airfoil
| Details | Dat file | Parser | |
|
(e664-il) EPPLER 664 AIRFOIL Eppler E664 variable geometry sailplane airfoil Max thickness 16.6% at 45.6% chord. Max camber 2.6% at 40.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 664 AIRFOIL
32.0 30.0
0.0002300 0.0022900
0.0046800 0.0115500
0.0137100 0.0218300
0.0271400 0.0326100
0.0448700 0.0434800
0.0667400 0.0541600
0.0925800 0.0644100
0.1221600 0.0740100
0.1552100 0.0827700
0.1914500 0.0905500
0.2305100 0.0972000
0.2720500 0.1026200
0.3156400 0.1067000
0.3608700 0.1093800
0.4072700 0.1106000
0.4563700 0.1102900
0.5016700 0.1084000
0.5486900 0.1048200
0.5949700 0.0993700
0.6404300 0.0916700
0.6854900 0.0819700
0.7300800 0.0712200
0.7735300 0.0602000
0.8151200 0.0494200
0.8540700 0.0392700
0.8896400 0.0300500
0.9211000 0.0219300
0.9477400 0.0149100
0.9692300 0.0088100
0.9855700 0.0039100
0.9962300 0.0009200
1.0000000 0.0000000
0.0002300 0.0022900
0.0014600 -.0052100
0.0090300 -.0117300
0.0223400 -.0181700
0.0409700 -.0242300
0.0647100 -.0297900
0.0933400 -.0348200
0.1265100 -.0393600
0.1638000 -.0434100
0.2047400 -.0469300
0.2488200 -.0499000
0.2955200 -.0522900
0.3442900 -.0540600
0.3945200 -.0552200
0.4455600 -.0557200
0.4967800 -.0554600
0.5475400 -.0543300
0.5971900 -.0521900
0.6451200 -.0486700
0.6911700 -.0432200
0.7356100 -.0356700
0.7790900 -.0262300
0.8221900 -.0163700
0.8639900 -.0080800
0.9026000 -.0022400
0.9364100 0.0010200
0.9638500 0.0019800
0.9840000 0.0014200
0.9960200 0.0004500
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 664 AIRFOIL (e664-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e664-il | 50,000 | 9 | 19.3 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 50,000 | 5 | 19.7 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 100,000 | 9 | 39.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 100,000 | 5 | 33.2 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 200,000 | 9 | 57.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 200,000 | 5 | 58.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 500,000 | 9 | 90.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 500,000 | 5 | 90.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 1,000,000 | 9 | 120.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 1,000,000 | 5 | 111.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||