EPPLER 396 AIRFOIL (e396-il)
EPPLER 396 AIRFOIL - Eppler E396 human powered aircraft airfoil
| Details | Dat file | Parser | |
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(e396-il) EPPLER 396 AIRFOIL Eppler E396 human powered aircraft airfoil Max thickness 13.1% at 29.5% chord. Max camber 5.4% at 52.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 396 AIRFOIL
37. 36.
0.0000000 -.0000600
0.0000300 0.0006500
0.0002400 0.0021500
0.0006500 0.0037500
0.0016100 0.0063100
0.0034400 0.0098000
0.0112200 0.0197200
0.0232500 0.0304000
0.0394100 0.0414100
0.0595800 0.0524400
0.0835900 0.0631800
0.1112400 0.0734200
0.1423100 0.0829300
0.1765000 0.0915400
0.2135100 0.0990700
0.2529700 0.1053800
0.2945000 0.1102900
0.3377400 0.1136500
0.3823600 0.1153200
0.4280100 0.1152500
0.4743400 0.1134100
0.5210200 0.1098300
0.5676800 0.1045300
0.6140400 0.0976100
0.6599000 0.0892600
0.7049400 0.0799200
0.7486799 0.0700000
0.7905700 0.0598600
0.8300700 0.0498300
0.8666200 0.0402000
0.8996400 0.0312400
0.9285900 0.0231300
0.9529100 0.0159400
0.9723800 0.0095700
0.9870900 0.0043600
0.9966300 0.0010700
1.0000000 0.0000000
0.0000000 -.0000600
0.0000400 -.0007400
0.0001500 -.0013700
0.0003500 -.0019800
0.0006500 -.0026000
0.0010200 -.0032200
0.0019500 -.0044800
0.0031200 -.0057500
0.0052700 -.0076700
0.0111000 -.0115200
0.0245200 -.0171900
0.0427900 -.0219000
0.0658100 -.0254400
0.0934800 -.0276900
0.1256600 -.0286300
0.1621500 -.0282600
0.2027300 -.0266500
0.2471100 -.0239200
0.2949500 -.0202900
0.3458000 -.0160000
0.3991100 -.0113300
0.4542500 -.0065300
0.5105400 -.0018400
0.5672600 0.0025200
0.6236500 0.0063300
0.6789400 0.0094300
0.7323101 0.0116600
0.7829400 0.0129300
0.8300200 0.0132000
0.8727600 0.0124900
0.9104000 0.0108800
0.9422500 0.0085200
0.9675600 0.0056300
0.9856800 0.0028000
0.9964400 0.0007500
1.0000000 0.0000000
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Polars for EPPLER 396 AIRFOIL (e396-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e396-il | 50,000 | 9 | 25.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 50,000 | 5 | 22.7 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 100,000 | 9 | 54.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 100,000 | 5 | 57.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 200,000 | 9 | 89.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 200,000 | 5 | 90.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 500,000 | 9 | 135.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 500,000 | 5 | 128.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 1,000,000 | 9 | 169.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 1,000,000 | 5 | 148 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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