GOE 600 AIRFOIL (goe600-il)
GOE 600 AIRFOIL - Gottingen 600 airfoil
| Details | Dat file | Parser | |
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(goe600-il) GOE 600 AIRFOIL Gottingen 600 airfoil Max thickness 13.1% at 29.4% chord. Max camber 1.9% at 49.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 600 AIRFOIL
17. 17.
0.0000100 0.0000000
0.0111200 0.0178600
0.0229700 0.0262800
0.0469800 0.0391400
0.0712900 0.0480200
0.0957100 0.0554200
0.1448800 0.0662300
0.1943100 0.0735600
0.2937100 0.0812600
0.3936100 0.0825000
0.4938600 0.0792700
0.5946100 0.0695800
0.6957100 0.0554200
0.7969600 0.0392600
0.8983999 0.0206300
0.9491000 0.0115600
1.0000000 0.0025000
0.0000100 0.0000000
0.0137100 -.0154400
0.0267100 -.0219300
0.0523300 -.0299400
0.0778000 -.0359700
0.1030700 -.0395100
0.1534300 -.0441100
0.2037000 -.0477100
0.3038400 -.0494500
0.4036300 -.0467200
0.5031800 -.0410000
0.6025800 -.0333000
0.7019899 -.0256000
0.8013900 -.0178900
0.9007900 -.0101900
0.9504901 -.0063400
1.0000000 -.0025000
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Similar airfoils
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Polars for GOE 600 AIRFOIL (goe600-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe600-il | 50,000 | 9 | 32.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 50,000 | 5 | 33.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 100,000 | 5 | 49.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 200,000 | 9 | 69.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 200,000 | 5 | 62.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 500,000 | 9 | 91.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 500,000 | 5 | 76.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 1,000,000 | 9 | 99.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 1,000,000 | 5 | 86 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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