GOE 611 AIRFOIL (goe611-il)
GOE 611 AIRFOIL - Gottingen 611 airfoil
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(goe611-il) GOE 611 AIRFOIL Gottingen 611 airfoil Max thickness 12.9% at 29.9% chord. Max camber 5.8% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 611 AIRFOIL
16. 16.
0.0000000 0.0000000
0.0123800 0.0250600
0.0248100 0.0396200
0.0497200 0.0597400
0.0746500 0.0743500
0.0996000 0.0839700
0.1495200 0.1002100
0.1994700 0.1114500
0.2994200 0.1224200
0.3994200 0.1224000
0.4994600 0.1143700
0.5995200 0.1008500
0.6996100 0.0818200
0.7997200 0.0583000
0.8998400 0.0332700
1.0000000 0.0032500
0.0000000 0.0000000
0.0125400 -.0074400
0.0250400 -.0078800
0.0500400 -.0077600
0.0750400 -.0076400
0.1000400 -.0075200
0.1500300 -.0072900
0.2000300 -.0070500
0.3000300 -.0065700
0.4000300 -.0061000
0.5000300 -.0056200
0.6000200 -.0051500
0.7000200 -.0046700
0.8000200 -.0042000
0.9000200 -.0037200
1.0000000 -.0032500
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Polars for GOE 611 AIRFOIL (goe611-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe611-il | 50,000 | 9 | 10 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 50,000 | 5 | 31.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe611-il | 100,000 | 9 | 52.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 100,000 | 5 | 56.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe611-il | 200,000 | 9 | 77.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 200,000 | 5 | 75.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe611-il | 500,000 | 9 | 106.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 500,000 | 5 | 97 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe611-il | 1,000,000 | 9 | 125.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 1,000,000 | 5 | 107.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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