EPPLER 398 AIRFOIL (e398-il)
EPPLER 398 AIRFOIL - Eppler E398 human powered aircraft airfoil
| Details | Dat file | Parser | |
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(e398-il) EPPLER 398 AIRFOIL Eppler E398 human powered aircraft airfoil Max thickness 14.2% at 29.6% chord. Max camber 5.3% at 50.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 398 AIRFOIL
36. 37.
0.0000100 0.0004400
0.0001800 0.0020300
0.0005500 0.0037200
0.0014600 0.0064000
0.0030800 0.0098000
0.0106000 0.0201400
0.0223800 0.0312700
0.0382800 0.0427700
0.0581700 0.0542800
0.0818800 0.0655200
0.1092100 0.0762400
0.1399000 0.0862300
0.1736800 0.0952600
0.2102100 0.1031600
0.2491600 0.1097400
0.2901500 0.1148200
0.3328400 0.1182200
0.3768800 0.1197800
0.4219700 0.1193900
0.4678300 0.1169600
0.5142700 0.1125200
0.5611200 0.1062400
0.6080800 0.0984900
0.6546900 0.0896200
0.7004700 0.0799600
0.7449000 0.0698300
0.7874600 0.0595700
0.8275800 0.0494800
0.8646900 0.0398600
0.8982100 0.0309200
0.9275801 0.0228700
0.9522600 0.0157500
0.9720100 0.0094500
0.9869200 0.0042900
0.9965799 0.0010500
1.0000000 0.0000000
0.0000100 0.0004400
0.0000100 -.0003200
0.0000600 -.0010400
0.0001900 -.0017200
0.0004200 -.0023800
0.0007400 -.0030400
0.0011200 -.0037200
0.0020900 -.0050700
0.0033000 -.0064400
0.0055200 -.0085000
0.0117700 -.0128300
0.0255300 -.0190400
0.0441000 -.0243100
0.0673500 -.0284500
0.0951700 -.0313300
0.1274100 -.0328900
0.1638300 -.0331100
0.2042100 -.0320400
0.2482500 -.0297300
0.2956400 -.0263400
0.3460100 -.0221100
0.3988400 -.0173300
0.4535400 -.0122600
0.5094500 -.0071800
0.5658800 -.0023200
0.6220800 0.0020900
0.6772700 0.0058200
0.7306401 0.0087000
0.7813800 0.0106100
0.8286400 0.0114700
0.8716200 0.0112700
0.9095400 0.0100900
0.9416700 0.0080500
0.9672200 0.0054000
0.9855300 0.0027000
0.9964100 0.0007200
1.0000000 0.0000000
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Polars for EPPLER 398 AIRFOIL (e398-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e398-il | 50,000 | 9 | 6.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 50,000 | 5 | 17.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 100,000 | 9 | 47.5 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 100,000 | 5 | 54.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 200,000 | 9 | 84.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 200,000 | 5 | 86.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 500,000 | 9 | 129 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 500,000 | 5 | 124.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 1,000,000 | 9 | 163.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 1,000,000 | 5 | 147 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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