EPPLER 593 AIRFOIL (e593-il)
EPPLER 593 AIRFOIL - Eppler E593 airfoil
| Details | Dat file | Parser | |
|
(e593-il) EPPLER 593 AIRFOIL Eppler E593 airfoil Max thickness 11.3% at 24.2% chord. Max camber 4.6% at 29.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 593 AIRFOIL
34. 38.
0.0000100 0.0000400
0.0001000 0.0015800
0.0006000 0.0042700
0.0048100 0.0135000
0.0130200 0.0237800
0.0251500 0.0345500
0.0411200 0.0454200
0.0608200 0.0560600
0.0840800 0.0662100
0.1107200 0.0755900
0.1404700 0.0839800
0.1730600 0.0911500
0.2081400 0.0968700
0.2453500 0.1008900
0.2842800 0.1028000
0.3248300 0.1020700
0.3671500 0.0983700
0.4116900 0.0916000
0.4590700 0.0824400
0.5090400 0.0722500
0.5606100 0.0619200
0.6128000 0.0519100
0.6646600 0.0425500
0.7152800 0.0340600
0.7638100 0.0265800
0.8094200 0.0201600
0.8513700 0.0148200
0.8890000 0.0104800
0.9217100 0.0070300
0.9490899 0.0043000
0.9709200 0.0022200
0.9869200 0.0008400
0.9967000 0.0001700
1.0000000 0.0000000
0.0000100 0.0000400
0.0000900 -.0013800
0.0002000 -.0020500
0.0003700 -.0026800
0.0006000 -.0032500
0.0009200 -.0038000
0.0013300 -.0043300
0.0018100 -.0048600
0.0029800 -.0059200
0.0043800 -.0069600
0.0069000 -.0085000
0.0182200 -.0129400
0.0348400 -.0163100
0.0566000 -.0182300
0.0836300 -.0186900
0.1160000 -.0178900
0.1535400 -.0163000
0.1957500 -.0142600
0.2420800 -.0120200
0.2919600 -.0098700
0.3445900 -.0081000
0.3989900 -.0067800
0.4543700 -.0057500
0.5100700 -.0049000
0.5646100 -.0042000
0.6198800 -.0036200
0.6727101 -.0031400
0.7233300 -.0027500
0.7711700 -.0024200
0.8156500 -.0021500
0.8562600 -.0019000
0.8925200 -.0016600
0.9239900 -.0013600
0.9503900 -.0009400
0.9715300 -.0004600
0.9871100 -.0001100
0.9967400 0.0000000
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 593 AIRFOIL (e593-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e593-il | 50,000 | 9 | 7.3 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 50,000 | 5 | 16.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 100,000 | 9 | 25 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 100,000 | 5 | 36.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 200,000 | 9 | 71.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 200,000 | 5 | 74.2 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 500,000 | 9 | 115.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 500,000 | 5 | 113.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 1,000,000 | 9 | 148.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 1,000,000 | 5 | 140.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||