EPPLER 1211 AIRFOIL (e1211-il)
EPPLER 1211 AIRFOIL - Eppler E1211 general aviation airfoil
| Details | Dat file | Parser | |
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(e1211-il) EPPLER 1211 AIRFOIL Eppler E1211 general aviation airfoil Max thickness 18% at 20.9% chord. Max camber 4.4% at 37.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 1211 AIRFOIL
32.0 29.0
0.0000000 0.0000000
0.0063135 0.0237338
0.0151275 0.0385619
0.0276716 0.0534990
0.0438257 0.0681453
0.0634297 0.0820806
0.0863135 0.0949550
0.1122470 0.1062887
0.1412500 0.1155815
0.1734125 0.1226635
0.2086145 0.1274446
0.2467660 0.1298649
0.2877370 0.1300145
0.3312375 0.1280234
0.3769575 0.1240516
0.4245671 0.1182893
0.4736364 0.1109867
0.5237353 0.1024437
0.5743440 0.0929706
0.6248927 0.0829075
0.6747711 0.0725745
0.7233296 0.0623019
0.7698681 0.0523698
0.8137068 0.0430085
0.8541455 0.0344080
0.8905243 0.0266685
0.9222433 0.0198503
0.9487324 0.0138234
0.9698614 0.0083379
0.9858506 0.0037437
0.9962901 0.0008810
1.0000000 -.0000000
0.0000000 0.0000000
0.0043437 -.0143666
0.0141414 -.0243593
0.0286093 -.0337932
0.0473176 -.0421381
0.0700464 -.0489141
0.0967358 -.0537110
0.1274059 -.0561589
0.1623067 -.0559778
0.2019283 -.0534178
0.2461903 -.0492990
0.2944627 -.0442612
0.3460453 -.0386442
0.4002080 -.0327679
0.4561908 -.0268820
0.5131935 -.0212064
0.5704262 -.0159109
0.6270687 -.0111452
0.6823010 -.0070292
0.7353431 -.0036226
0.7854049 -.0009953
0.8317464 0.0008629
0.8736576 0.0019822
0.9104786 0.0024229
0.9416093 0.0023049
0.9665597 0.0018186
0.9848899 0.0010939
0.9961800 0.0003410
1.0000000 -.0000000
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Polars for EPPLER 1211 AIRFOIL (e1211-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1211-il | 50,000 | 9 | 6 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 50,000 | 5 | 24.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 100,000 | 9 | 33.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 100,000 | 5 | 44 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 200,000 | 9 | 58.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 200,000 | 5 | 62.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 500,000 | 9 | 89 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 500,000 | 5 | 89.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 1,000,000 | 9 | 115.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 1,000,000 | 5 | 113.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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