EPPLER 266 AIRFOIL (e266-il)
EPPLER 266 AIRFOIL - Eppler E266 general purpose airfoil
| Details | Dat file | Parser | |
|
(e266-il) EPPLER 266 AIRFOIL Eppler E266 general purpose airfoil Max thickness 17.3% at 39.8% chord. Max camber 3.1% at 39.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 266 AIRFOIL
32. 30.
0.0002400 0.0023000
0.0048000 0.0116400
0.0138900 0.0222200
0.0273200 0.0334400
0.0449600 0.0448900
0.0666500 0.0562500
0.0921900 0.0672700
0.1213300 0.0777000
0.1538000 0.0873400
0.1892600 0.0960100
0.2273600 0.1035000
0.2677100 0.1096700
0.3098900 0.1143500
0.3534500 0.1173900
0.3978900 0.1185600
0.4428400 0.1175500
0.4880100 0.1140400
0.5335500 0.1075900
0.5801100 0.0985400
0.6276500 0.0880600
0.6753700 0.0770400
0.7224600 0.0660000
0.7680500 0.0553400
0.8113300 0.0453500
0.8515000 0.0362000
0.8877900 0.0279900
0.9195099 0.0206400
0.9463300 0.0138900
0.9683200 0.0078900
0.9852300 0.0033200
0.9961700 0.0007500
1.0000000 0.0000000
0.0002400 0.0023000
0.0014700 -.0050100
0.0092700 -.0112100
0.0230200 -.0174000
0.0422000 -.0233200
0.0664900 -.0288700
0.0956000 -.0339800
0.1291700 -.0386400
0.1667800 -.0428000
0.2079400 -.0464200
0.2521800 -.0494600
0.2989700 -.0518800
0.3477600 -.0536200
0.3979700 -.0546400
0.4490300 -.0549000
0.5003200 -.0543400
0.5512600 -.0528900
0.6012300 -.0504600
0.6496100 -.0467800
0.6962500 -.0414000
0.7413900 -.0343400
0.7851800 -.0261100
0.8276500 -.0176100
0.8681200 -.0101000
0.9053100 -.0043800
0.9379200 -.0007600
0.9646200 -.0008100
0.9842100 -.0008600
0.9960600 -.0003100
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 266 AIRFOIL (e266-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e266-il | 50,000 | 9 | 13.9 at α=15.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 50,000 | 5 | 13.4 at α=14° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 100,000 | 9 | 26 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 100,000 | 5 | 23.5 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 200,000 | 9 | 61.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 200,000 | 5 | 59.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 500,000 | 9 | 100.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 500,000 | 5 | 100 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 1,000,000 | 9 | 131.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 1,000,000 | 5 | 124.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||