GOE 401 AIRFOIL (goe401-il)
GOE 401 AIRFOIL - Gottingen 401 airfoil
| Details | Dat file | Parser | |
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(goe401-il) GOE 401 AIRFOIL Gottingen 401 airfoil Max thickness 7.1% at 29.9% chord. Max camber 4.9% at 29.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 401 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123000 0.0191300
0.0247000 0.0282600
0.0495700 0.0410200
0.0744600 0.0517800
0.0993600 0.0605400
0.1492400 0.0725700
0.1991600 0.0795900
0.2991200 0.0841400
0.3991600 0.0801900
0.4992300 0.0732400
0.5993400 0.0627900
0.6994800 0.0493400
0.7996399 0.0344000
0.8998001 0.0189500
0.9498800 0.0109700
1.0000000 0.0000000
0.0000000 0.0000000
0.0126200 -.0118700
0.0251300 -.0122400
0.0501100 -.0104700
0.0750800 -.0072100
0.1000400 -.0034500
0.1499600 0.0040700
0.1999000 0.0096000
0.2998600 0.0131500
0.3998600 0.0137000
0.4998700 0.0122500
0.5999000 0.0093000
0.6999300 0.0068500
0.7999600 0.0039000
0.8999900 0.0009500
0.9500100 -.0005200
1.0000000 0.0000000
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Polars for GOE 401 AIRFOIL (goe401-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe401-il | 50,000 | 9 | 32.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe401-il | 50,000 | 5 | 38.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe401-il | 100,000 | 9 | 53.9 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe401-il | 100,000 | 5 | 56 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe401-il | 200,000 | 9 | 74.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe401-il | 200,000 | 5 | 75.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe401-il | 500,000 | 9 | 104.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe401-il | 500,000 | 5 | 100.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe401-il | 1,000,000 | 9 | 127.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe401-il | 1,000,000 | 5 | 119 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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