GOE 509 AIRFOIL (goe509-il)
GOE 509 AIRFOIL - Gottingen 509 airfoil
| Details | Dat file | Parser | |
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(goe509-il) GOE 509 AIRFOIL Gottingen 509 airfoil Max thickness 11.1% at 29.9% chord. Max camber 5.2% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 509 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123700 0.0260600
0.0248200 0.0361200
0.0497300 0.0542500
0.0746700 0.0668700
0.0996100 0.0775000
0.1495500 0.0907500
0.1995000 0.0995000
0.2994700 0.1070000
0.3994800 0.1035000
0.4995200 0.0970000
0.5995800 0.0850000
0.6996601 0.0685000
0.7997500 0.0495000
0.8998600 0.0280000
0.9499400 0.0132500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125400 -.0089400
0.0250600 -.0118700
0.0500700 -.0137500
0.0750700 -.0141200
0.1000700 -.0140000
0.1500700 -.0132500
0.2000600 -.0110000
0.3000200 -.0035000
0.4000000 0.0000000
0.5000100 -.0025000
0.6000400 -.0080000
0.7000600 -.0110000
0.8000500 -.0105000
0.9000400 -.0080000
0.9500300 -.0057500
1.0000000 0.0000000
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Polars for GOE 509 AIRFOIL (goe509-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe509-il | 50,000 | 9 | 19.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 50,000 | 5 | 35.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 100,000 | 9 | 51.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 100,000 | 5 | 52.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 200,000 | 9 | 69.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 200,000 | 5 | 68.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 500,000 | 9 | 96.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 500,000 | 5 | 91.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 1,000,000 | 9 | 117.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 1,000,000 | 5 | 97.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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