EPPLER 544 AIRFOIL (e544-il)
EPPLER 544 AIRFOIL - Eppler E544 general aviation airfoil
| Details | Dat file | Parser | |
|
(e544-il) EPPLER 544 AIRFOIL Eppler E544 general aviation airfoil Max thickness 17.5% at 40% chord. Max camber 1.9% at 30.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 544 AIRFOIL
36. 37.
0.0000100 -.0001500
0.0000200 0.0005900
0.0002300 0.0021400
0.0006500 0.0038000
0.0016500 0.0064300
0.0032500 0.0094800
0.0111500 0.0193600
0.0235600 0.0298300
0.0403100 0.0404700
0.0612700 0.0509500
0.0862400 0.0610200
0.1150200 0.0704600
0.1473300 0.0790800
0.1828600 0.0867200
0.2212900 0.0932300
0.2622100 0.0984900
0.3052300 0.1023700
0.3498800 0.1047800
0.3956800 0.1055400
0.4422400 0.1044000
0.4893900 0.1011700
0.5371000 0.0959100
0.5851800 0.0890400
0.6331800 0.0809500
0.6806300 0.0719900
0.7270000 0.0625300
0.7717200 0.0529300
0.8141900 0.0435300
0.8537600 0.0346600
0.8897800 0.0265700
0.9215700 0.0194400
0.9485100 0.0133900
0.9699700 0.0083100
0.9858600 0.0039800
0.9962300 0.0010000
1.0000000 0.0000000
0.0000100 -.0001500
0.0000500 -.0008500
0.0001700 -.0015100
0.0004100 -.0021400
0.0007400 -.0027800
0.0011500 -.0034400
0.0021900 -.0047700
0.0035000 -.0061300
0.0059100 -.0082100
0.0131100 -.0129900
0.0283200 -.0201900
0.0486400 -.0272600
0.0737800 -.0340800
0.1034600 -.0405300
0.1373000 -.0465700
0.1748700 -.0521600
0.2156500 -.0572100
0.2591200 -.0615900
0.3047600 -.0652100
0.3520100 -.0679300
0.4003000 -.0696100
0.4490700 -.0701000
0.4977100 -.0692100
0.5456300 -.0665000
0.5928200 -.0613200
0.6397700 -.0536200
0.6869700 -.0440300
0.7343600 -.0338700
0.7809900 -.0242700
0.8257800 -.0158800
0.8676000 -.0091400
0.9053200 -.0042500
0.9378501 -.0011700
0.9642800 -.0003500
0.9838500 0.0006700
0.9959200 0.0002900
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 544 AIRFOIL (e544-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e544-il | 50,000 | 9 | 21.5 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e544-il | 50,000 | 5 | 18.5 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e544-il | 100,000 | 9 | 40.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e544-il | 100,000 | 5 | 37.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e544-il | 200,000 | 9 | 60.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e544-il | 200,000 | 5 | 61.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e544-il | 500,000 | 9 | 91 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e544-il | 500,000 | 5 | 86.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e544-il | 1,000,000 | 9 | 113.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e544-il | 1,000,000 | 5 | 101.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||