EPPLER 325 AIRFOIL (e325-il)
EPPLER 325 AIRFOIL - Eppler E325 flying wing airfoil
| Details | Dat file | Parser | |
|
(e325-il) EPPLER 325 AIRFOIL Eppler E325 flying wing airfoil Max thickness 12.6% at 34.3% chord. Max camber 1.8% at 16.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 325 AIRFOIL
34. 39.
0.0000100 -.0004100
0.0000200 0.0009600
0.0002100 0.0024100
0.0008300 0.0047200
0.0048400 0.0120000
0.0135500 0.0213200
0.0264100 0.0309200
0.0433500 0.0403700
0.0641700 0.0493600
0.0887500 0.0576000
0.1168700 0.0647800
0.1483200 0.0706600
0.1829200 0.0749300
0.2205600 0.0774000
0.2611200 0.0780000
0.3044900 0.0767200
0.3505000 0.0738100
0.3988700 0.0695200
0.4488900 0.0641100
0.5003400 0.0578600
0.5525900 0.0510800
0.6050000 0.0440600
0.6569200 0.0370900
0.7076300 0.0304200
0.7563900 0.0242800
0.8024600 0.0188100
0.8451000 0.0141400
0.8836100 0.0102700
0.9173300 0.0071900
0.9456800 0.0047000
0.9683999 0.0025800
0.9854300 0.0009400
0.9962500 0.0001500
1.0000000 0.0000000
0.0000100 -.0004100
0.0000700 -.0010500
0.0002000 -.0016600
0.0003900 -.0022200
0.0006900 -.0027400
0.0010800 -.0032700
0.0015500 -.0038100
0.0027100 -.0048700
0.0041400 -.0059500
0.0067300 -.0075900
0.0081400 -.0083700
0.0212700 -.0138200
0.0398100 -.0191000
0.0635200 -.0240800
0.0921500 -.0287500
0.1254200 -.0331700
0.1628800 -.0374300
0.2039200 -.0415400
0.2479800 -.0454100
0.2944600 -.0489200
0.3428200 -.0518900
0.3925500 -.0542400
0.4431300 -.0558800
0.4940200 -.0567600
0.5446700 -.0568100
0.5945400 -.0560000
0.6430900 -.0542800
0.6898000 -.0515800
0.7341200 -.0477000
0.7759600 -.0422600
0.8157100 -.0354600
0.8532900 -.0281800
0.8880700 -.0211200
0.9193800 -.0147500
0.9464500 -.0093500
0.9686700 -.0050400
0.9855200 -.0019900
0.9962700 -.0004100
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 325 AIRFOIL (e325-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e325-il | 50,000 | 9 | 17.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 50,000 | 5 | 26.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 100,000 | 9 | 39.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 100,000 | 5 | 42.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 200,000 | 9 | 58.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 200,000 | 5 | 51.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 500,000 | 9 | 69.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 500,000 | 5 | 69.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 1,000,000 | 9 | 88.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 1,000,000 | 5 | 82.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||