GOE 758 AIRFOIL (goe758-il)
GOE 758 AIRFOIL - Gottingen 758 airfoil
| Details | Dat file | Parser | |
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(goe758-il) GOE 758 AIRFOIL Gottingen 758 airfoil Max thickness 13.9% at 30% chord. Max camber 4.7% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 758 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0229300
0.0250000 0.0343600
0.0500000 0.0517300
0.0750000 0.0645900
0.1000000 0.0759500
0.1500000 0.0931800
0.2000000 0.1044000
0.3000000 0.1143500
0.4000000 0.1133000
0.5000000 0.1032500
0.6000000 0.0867000
0.7000000 0.0686500
0.8000000 0.0466000
0.9000000 0.0235500
0.9500000 0.0122700
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0145700
0.0250000 -.0176400
0.0500000 -.0217800
0.0750000 -.0244100
0.1000000 -.0255500
0.1500000 -.0268200
0.2000000 -.0271000
0.3000000 -.0241500
0.4000000 -.0197000
0.5000000 -.0142500
0.6000000 -.0083000
0.7000000 -.0038500
0.8000000 -.0014000
0.9000000 -.0004500
0.9500000 -.0002300
1.0000000 0.0000000
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Polars for GOE 758 AIRFOIL (goe758-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe758-il | 50,000 | 9 | 7.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 50,000 | 5 | 25.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 100,000 | 9 | 45.4 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 100,000 | 5 | 52.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 200,000 | 9 | 73.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 200,000 | 5 | 75.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 500,000 | 9 | 108.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 500,000 | 5 | 102.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 1,000,000 | 9 | 133.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 1,000,000 | 5 | 123.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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