EPPLER 656 AIRFOIL (e656-il)
EPPLER 656 AIRFOIL - Eppler E656 sailplane airfoil
| Details | Dat file | Parser | |
|
(e656-il) EPPLER 656 AIRFOIL Eppler E656 sailplane airfoil Max thickness 16.2% at 37% chord. Max camber 4.8% at 42.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 656 AIRFOIL
35. 38.
0.0000100 -.0000600
0.0000900 0.0016700
0.0005600 0.0044500
0.0024200 0.0099200
0.0091300 0.0209600
0.0200300 0.0328000
0.0350200 0.0450000
0.0540200 0.0571800
0.0768800 0.0690600
0.1034200 0.0803700
0.1334400 0.0908900
0.1666700 0.1004400
0.2028000 0.1088400
0.2415100 0.1159300
0.2824200 0.1216000
0.3251200 0.1257300
0.3691900 0.1282100
0.4141900 0.1289300
0.4596200 0.1277800
0.5050800 0.1245200
0.5503200 0.1189300
0.5953000 0.1107900
0.6404100 0.1003100
0.6856900 0.0884300
0.7305200 0.0760000
0.7742000 0.0636000
0.8159600 0.0517100
0.8550300 0.0407000
0.8906500 0.0308300
0.9220800 0.0222600
0.9486300 0.0149600
0.9699600 0.0087600
0.9860300 0.0038900
0.9963700 0.0009300
1.0000000 0.0000000
0.0000100 -.0000600
0.0001000 -.0016700
0.0002300 -.0024300
0.0004100 -.0031400
0.0006600 -.0037900
0.0010100 -.0044100
0.0014700 -.0050300
0.0020000 -.0056400
0.0032800 -.0068600
0.0048300 -.0080700
0.0076100 -.0098700
0.0128100 -.0125600
0.0282400 -.0180000
0.0490200 -.0227200
0.0749000 -.0266600
0.1056100 -.0298000
0.1408400 -.0321600
0.1802200 -.0337600
0.2233100 -.0336800
0.2696200 -.0349600
0.3185900 -.0346700
0.3696500 -.0338500
0.4221700 -.0325500
0.4754900 -.0307600
0.5290100 -.0284400
0.5821500 -.0256000
0.6343500 -.0222200
0.6850500 -.0183100
0.7337800 -.0137200
0.7805800 -.0084500
0.8254000 -.0033200
0.8674000 0.0008100
0.9055200 0.0034500
0.9385900 0.0043600
0.9653400 0.0036700
0.9846900 0.0020700
0.9962000 0.0005900
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 656 AIRFOIL (e656-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e656-il | 50,000 | 9 | 5.7 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 50,000 | 5 | 14.6 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 100,000 | 9 | 34.7 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 100,000 | 5 | 29.8 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 200,000 | 9 | 69.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 200,000 | 5 | 70.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 500,000 | 9 | 125.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 500,000 | 5 | 118.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 1,000,000 | 9 | 161.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 1,000,000 | 5 | 147.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||