EPPLER 399 AIRFOIL (e399-il)
EPPLER 399 AIRFOIL - Eppler E399 human powered aircraft airfoil
| Details | Dat file | Parser | |
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(e399-il) EPPLER 399 AIRFOIL Eppler E399 human powered aircraft airfoil Max thickness 14.8% at 29% chord. Max camber 5.1% at 51.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 399 AIRFOIL
37. 36.
0.0000100 -.0001800
0.0000200 0.0006100
0.0002100 0.0022500
0.0006200 0.0039900
0.0015700 0.0067300
0.0028500 0.0094600
0.0102500 0.0199200
0.0219500 0.0312000
0.0377900 0.0428300
0.0576500 0.0544800
0.0813400 0.0658600
0.1086600 0.0767200
0.1393600 0.0868300
0.1731500 0.0959800
0.2097100 0.1039900
0.2486900 0.1106700
0.2897200 0.1158300
0.3324500 0.1193000
0.3765400 0.1209200
0.4216700 0.1205700
0.4675700 0.1181800
0.5140600 0.1137400
0.5609600 0.1074600
0.6079600 0.0997000
0.6546000 0.0908000
0.7004100 0.0811000
0.7448700 0.0709100
0.7874401 0.0605700
0.8275700 0.0504000
0.8646801 0.0406700
0.8982000 0.0316300
0.9275600 0.0234600
0.9522200 0.0162000
0.9719500 0.0097500
0.9868600 0.0044400
0.9965600 0.0010900
1.0000000 0.0000000
0.0000100 -.0001800
0.0000500 -.0009300
0.0001700 -.0016300
0.0003800 -.0023200
0.0006900 -.0030200
0.0010700 -.0037300
0.0020200 -.0051600
0.0032100 -.0066000
0.0054000 -.0087900
0.0124600 -.0139600
0.0264500 -.0206600
0.0451800 -.0264800
0.0685100 -.0312200
0.0963100 -.0347200
0.1284000 -.0369000
0.1645600 -.0377300
0.2045200 -.0371900
0.2479900 -.0353000
0.2947100 -.0321000
0.3444100 -.0278500
0.3966200 -.0228500
0.4507800 -.0174000
0.5062600 -.0117800
0.5624000 -.0062800
0.6184700 -.0011600
0.6737000 0.0033100
0.7272800 0.0069200
0.7783600 0.0094800
0.8260800 0.0109000
0.8696000 0.0111200
0.9080900 0.0102200
0.9407499 0.0083100
0.9667500 0.0056200
0.9853500 0.0028300
0.9963700 0.0007600
1.0000000 0.0000000
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Polars for EPPLER 399 AIRFOIL (e399-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e399-il | 50,000 | 9 | 6.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 50,000 | 5 | 16.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e399-il | 100,000 | 9 | 46.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 100,000 | 5 | 54 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e399-il | 200,000 | 9 | 83.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 200,000 | 5 | 85.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e399-il | 500,000 | 9 | 127.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 500,000 | 5 | 123.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e399-il | 1,000,000 | 9 | 161.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 1,000,000 | 5 | 142.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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