EPPLER 541 AIRFOIL (e541-il)
EPPLER 541 AIRFOIL - Eppler E541 general aviation airfoil
Details | Dat file | Parser | |
(e541-il) EPPLER 541 AIRFOIL Eppler E541 general aviation airfoil Max thickness 16.6% at 46.2% chord. Max camber 1.7% at 36.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 541 AIRFOIL 36. 37. 0.0000100 0.0002200 0.0000600 0.0008800 0.0003400 0.0022800 0.0008400 0.0037800 0.0019500 0.0061600 0.0026300 0.0073500 0.0101600 0.0161400 0.0223600 0.0255900 0.0390700 0.0352600 0.0601500 0.0448600 0.0853900 0.0541500 0.1145800 0.0629300 0.1474500 0.0710300 0.1836700 0.0783200 0.2229000 0.0846700 0.2647400 0.0899900 0.3087600 0.0941800 0.3545000 0.0971700 0.4014800 0.0989100 0.4491600 0.0993200 0.4970400 0.0983200 0.5445500 0.0957400 0.5913200 0.0913200 0.6372400 0.0848400 0.6825100 0.0764400 0.7270700 0.0668000 0.7704300 0.0566100 0.8120100 0.0463600 0.8511500 0.0365300 0.8871700 0.0275300 0.9193100 0.0196600 0.9468200 0.0131100 0.9689800 0.0078300 0.9854800 0.0036100 0.9961700 0.0008800 1.0000000 0.0000000 0.0000100 0.0002200 0.0000100 -.0004100 0.0001100 -.0009900 0.0003100 -.0015500 0.0006100 -.0021300 0.0009900 -.0027100 0.0019600 -.0039100 0.0032000 -.0051400 0.0055100 -.0070300 0.0148700 -.0126100 0.0308000 -.0192100 0.0518500 -.0256700 0.0777700 -.0318800 0.1082800 -.0377700 0.1430200 -.0433200 0.1815300 -.0485000 0.2233100 -.0532500 0.2678200 -.0574800 0.3145300 -.0610900 0.3628700 -.0639900 0.4122700 -.0660700 0.4621500 -.0672400 0.5119400 -.0673900 0.5610400 -.0663700 0.6088900 -.0640300 0.6548600 -.0599400 0.6990300 -.0533900 0.7421200 -.0443900 0.7847800 -.0338300 0.8268800 -.0233900 0.8672000 -.0143700 0.9043600 -.0073900 0.9370000 -.0027300 0.9638301 0.0002600 0.9837200 0.0004600 0.9959100 0.0002400 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 541 AIRFOIL (e541-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
e541-il | 50,000 | 9 | 25.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e541-il | 50,000 | 5 | 21 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
e541-il | 100,000 | 9 | 40.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e541-il | 100,000 | 5 | 29.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
e541-il | 200,000 | 9 | 46.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e541-il | 200,000 | 5 | 50.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
e541-il | 500,000 | 9 | 78.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e541-il | 500,000 | 5 | 79.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
e541-il | 1,000,000 | 9 | 106.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e541-il | 1,000,000 | 5 | 96.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
Reynolds number calculator |