GOE 410 AIRFOIL (goe410-il)
GOE 410 AIRFOIL - Gottingen 410 airfoil
| Details | Dat file | Parser | |
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(goe410-il) GOE 410 AIRFOIL Gottingen 410 airfoil Max thickness 16.1% at 30% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 410 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0260000
0.0250000 0.0365000
0.0500000 0.0505000
0.0750000 0.0590000
0.1000000 0.0650000
0.1500000 0.0725000
0.2000000 0.0780000
0.3000000 0.0805000
0.4000000 0.0745000
0.5000000 0.0630000
0.6000000 0.0500000
0.7000000 0.0360000
0.8000000 0.0220000
0.9000000 0.0100000
0.9500000 0.0045000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0260000
0.0250000 -.0365000
0.0500000 -.0505000
0.0750000 -.0590000
0.1000000 -.0650000
0.1500000 -.0725000
0.2000000 -.0780000
0.3000000 -.0805000
0.4000000 -.0745000
0.5000000 -.0630000
0.6000000 -.0500000
0.7000000 -.0360000
0.8000000 -.0220000
0.9000000 -.0100000
0.9500000 -.0045000
1.0000000 0.0000000
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Polars for GOE 410 AIRFOIL (goe410-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe410-il | 50,000 | 9 | 20.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe410-il | 50,000 | 5 | 25.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe410-il | 100,000 | 9 | 37.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe410-il | 100,000 | 5 | 35.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe410-il | 200,000 | 9 | 46.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe410-il | 200,000 | 5 | 45.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe410-il | 500,000 | 9 | 62.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe410-il | 500,000 | 5 | 65.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe410-il | 1,000,000 | 9 | 82 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe410-il | 1,000,000 | 5 | 81.8 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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