GOE 780 AIRFOIL (goe780-il)
GOE 780 AIRFOIL - Gottingen 780 airfoil
| Details | Dat file | Parser | |
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(goe780-il) GOE 780 AIRFOIL Gottingen 780 airfoil Max thickness 12% at 50% chord. Max camber 1% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 780 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0080000
0.0250000 0.0130000
0.0500000 0.0200000
0.0750000 0.0250000
0.1000000 0.0300000
0.1500000 0.0400000
0.2000000 0.0480000
0.3000000 0.0600000
0.4000000 0.0680000
0.5000000 0.0700000
0.6000000 0.0650000
0.7000000 0.0520000
0.8000000 0.0340000
0.9000000 0.0170000
0.9500000 0.0080000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0090000
0.0250000 -.0130000
0.0500000 -.0180000
0.0750000 -.0230000
0.1000000 -.0260000
0.1500000 -.0320000
0.2000000 -.0370000
0.3000000 -.0440000
0.4000000 -.0480000
0.5000000 -.0500000
0.6000000 -.0490000
0.7000000 -.0440000
0.8000000 -.0360000
0.9000000 -.0210000
0.9500000 -.0120000
1.0000000 0.0000000
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Similar airfoils
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Polars for GOE 780 AIRFOIL (goe780-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe780-il | 50,000 | 9 | 12.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 50,000 | 5 | 19.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 100,000 | 9 | 29.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 100,000 | 5 | 31.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 200,000 | 9 | 44.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 200,000 | 5 | 34.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 500,000 | 9 | 42.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 500,000 | 5 | 42.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 1,000,000 | 9 | 50.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 1,000,000 | 5 | 44 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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