EPPLER E1212MOD AIRFOIL (e1212mod-il)
EPPLER E1212MOD AIRFOIL - Eppler E1212 general aviation airfoil (as modified for use as Quickie wing airfoil)
| Details | Dat file | Parser | |
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(e1212mod-il) EPPLER E1212MOD AIRFOIL Eppler E1212 general aviation airfoil (as modified for use as Quickie wing airfoil) Max thickness 17.7% at 20.1% chord. Max camber 2.6% at 35.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER E1212MOD AIRFOIL
27. 27.
0.0000000 0.0000000
0.0002048 0.0007647
0.0010205 0.0032596
0.0050812 0.0129311
0.0076106 0.0176112
0.0126552 0.0247135
0.0252478 0.0394444
0.0503790 0.0603376
0.1005359 0.0853205
0.1506361 0.1012669
0.2006837 0.1088485
0.2506992 0.1113124
0.3006935 0.1104004
0.3506729 0.1071284
0.4006388 0.1016896
0.4505915 0.0941648
0.5005419 0.0862621
0.5504918 0.0782874
0.6004381 0.0697407
0.6503785 0.0602520
0.7003153 0.0501823
0.7502554 0.0406497
0.8002008 0.0319639
0.8501502 0.0239042
0.9001006 0.0160085
0.9500506 0.0080517
1.0000000 0.0000000
0.0000000 0.0000000
0.0000868 -.0180225
0.0008751 -.0198885
0.0048332 -.0265634
0.0073167 -.0291910
0.0122898 -.0334622
0.0247303 -.0429343
0.0496558 -.0548039
0.0995795 -.0669505
0.1495640 -.0694184
0.1995702 -.0684345
0.2495896 -.0653497
0.2996224 -.0601139
0.3496542 -.0550492
0.3996865 -.0499144
0.4497196 -.0446477
0.4997491 -.0399459
0.5497777 -.0354002
0.5998078 -.0306034
0.6498326 -.0266516
0.6998640 -.0216688
0.7498916 -.0172701
0.7999128 -.0138883
0.8499361 -.0101984
0.8999570 -.0068496
0.9499798 -.0032298
1.0000000 0.0000000
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Polars for EPPLER E1212MOD AIRFOIL (e1212mod-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1212mod-il | 50,000 | 9 | 5.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 50,000 | 5 | 20.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 100,000 | 9 | 28 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 100,000 | 5 | 39.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 200,000 | 9 | 51.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 200,000 | 5 | 57.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 500,000 | 9 | 81.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 500,000 | 5 | 84.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 1,000,000 | 9 | 108.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 1,000,000 | 5 | 107.6 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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