GOE 405 AIRFOIL (goe405-il)
GOE 405 AIRFOIL - Gottingen 405 airfoil
| Details | Dat file | Parser | |
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(goe405-il) GOE 405 AIRFOIL Gottingen 405 airfoil Max thickness 11.1% at 30% chord. Max camber 6.5% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 405 AIRFOIL
15. 15.
0.0000000 0.0000000
0.0125000 0.0212000
0.0250000 0.0324000
0.0500000 0.0498000
0.0750000 0.0647000
0.1000000 0.0771000
0.2000000 0.1067000
0.3000000 0.1188000
0.4000000 0.1199000
0.5000000 0.1140000
0.6000000 0.1011000
0.7000000 0.0822000
0.8000000 0.0593000
0.9000000 0.0314000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0098000
0.0250000 -.0126000
0.0500000 -.0147000
0.0750000 -.0148000
0.1000000 -.0134000
0.2000000 -.0018000
0.3000000 0.0078000
0.4000000 0.0109000
0.5000000 0.0115000
0.6000000 0.0106000
0.7000000 0.0092000
0.8000000 0.0068000
0.9000000 0.0039000
1.0000000 0.0000000
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Polars for GOE 405 AIRFOIL (goe405-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe405-il | 50,000 | 9 | 9.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 50,000 | 5 | 29.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe405-il | 100,000 | 9 | 54.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 100,000 | 5 | 58.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe405-il | 200,000 | 9 | 82.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 200,000 | 5 | 80.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe405-il | 500,000 | 9 | 115.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 500,000 | 5 | 104.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe405-il | 1,000,000 | 9 | 137.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 1,000,000 | 5 | 126.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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