GOE 619 AIRFOIL (goe619-il)
GOE 619 AIRFOIL - Gottingen 619 airfoil
| Details | Dat file | Parser | |
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(goe619-il) GOE 619 AIRFOIL Gottingen 619 airfoil Max thickness 13.7% at 19.5% chord. Max camber 4.5% at 49.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 619 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0114900 0.0225200
0.0233100 0.0375500
0.0475400 0.0546400
0.0719500 0.0677400
0.0964800 0.0783400
0.1458100 0.0930600
0.1954400 0.1012900
0.2951100 0.1087800
0.3951100 0.1087800
0.4954000 0.1022900
0.5959800 0.0893200
0.6967700 0.0718500
0.7977101 0.0509000
0.8987700 0.0274400
0.9493400 0.0147200
1.0000000 0.0000000
0.0000000 0.0000000
0.0133700 -.0194000
0.0261400 -.0253200
0.0514700 -.0326800
0.0766200 -.0360500
0.1016900 -.0374200
0.1517200 -.0381700
0.2016200 -.0359300
0.3012400 -.0274400
0.4008300 -.0184600
0.5004900 -.0109800
0.6003100 -.0069900
0.7001600 -.0034900
0.8000500 -.0010000
0.9000000 0.0000000
0.9499900 0.0002500
1.0000000 0.0000000
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Polars for GOE 619 AIRFOIL (goe619-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe619-il | 50,000 | 9 | 22 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 50,000 | 5 | 33.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe619-il | 100,000 | 9 | 52.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 100,000 | 5 | 51.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe619-il | 200,000 | 9 | 73.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 200,000 | 5 | 67.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe619-il | 500,000 | 9 | 99.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 500,000 | 5 | 82 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe619-il | 1,000,000 | 9 | 108.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 1,000,000 | 5 | 99.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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