GOE 604 AIRFOIL (goe604-il)
GOE 604 AIRFOIL - Gottingen 604 airfoil
| Details | Dat file | Parser | |
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(goe604-il) GOE 604 AIRFOIL Gottingen 604 airfoil Max thickness 17.8% at 29.3% chord. Max camber 5.4% at 29.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 604 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0108300 0.0330500
0.0225200 0.0491400
0.0463500 0.0723400
0.0704300 0.0905600
0.0947400 0.1042800
0.1438300 0.1222600
0.1932000 0.1347600
0.2927900 0.1427900
0.3930900 0.1368500
0.4938700 0.1214400
0.5949000 0.1010400
0.6960300 0.0786500
0.7972600 0.0542600
0.8986200 0.0273800
0.9493200 0.0134400
1.0000000 0.0000000
0.0000000 0.0000000
0.0132800 -.0154200
0.0261000 -.0216800
0.0514600 -.0289000
0.0767000 -.0336300
0.1018600 -.0368600
0.1519600 -.0388300
0.2019600 -.0388000
0.3017800 -.0352600
0.4015300 -.0302200
0.5012700 -.0251900
0.6010200 -.0201500
0.7007599 -.0151100
0.8005100 -.0100700
0.9002500 -.0050400
0.9501300 -.0025200
1.0000000 0.0000000
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Polars for GOE 604 AIRFOIL (goe604-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe604-il | 50,000 | 9 | 3.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 50,000 | 5 | 20.6 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 100,000 | 9 | 29.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 100,000 | 5 | 42.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 200,000 | 9 | 59.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 200,000 | 5 | 61.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 500,000 | 9 | 87.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 500,000 | 5 | 85.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 1,000,000 | 9 | 113 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 1,000,000 | 5 | 108.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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