GOE 491 AIRFOIL (goe491-il)
GOE 491 AIRFOIL - Gottingen 491 airfoil
| Details | Dat file | Parser | |
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(goe491-il) GOE 491 AIRFOIL Gottingen 491 airfoil Max thickness 4.9% at 20% chord. Max camber 2.9% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 491 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0140500
0.0250000 0.0196000
0.0500000 0.0287000
0.0750000 0.0353000
0.1000000 0.0404000
0.1500000 0.0471000
0.2000000 0.0513000
0.3000000 0.0537000
0.4000000 0.0506000
0.5000000 0.0465000
0.6000000 0.0404000
0.7000000 0.0328000
0.8000000 0.0237000
0.9000000 0.0131000
0.9500000 0.0078000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0059500
0.0250000 -.0079000
0.0500000 -.0073000
0.0750000 -.0052000
0.1000000 -.0031000
0.1500000 0.0001000
0.2000000 0.0028000
0.3000000 0.0052000
0.4000000 0.0051000
0.5000000 0.0025000
0.6000000 -.0011000
0.7000000 -.0032000
0.8000000 -.0048000
0.9000000 -.0044000
0.9500000 -.0032000
1.0000000 0.0000000
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Polars for GOE 491 AIRFOIL (goe491-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe491-il | 50,000 | 9 | 34.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe491-il | 50,000 | 5 | 37.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe491-il | 100,000 | 9 | 48.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe491-il | 100,000 | 5 | 50.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe491-il | 200,000 | 9 | 62.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe491-il | 200,000 | 5 | 62 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe491-il | 500,000 | 9 | 92.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe491-il | 500,000 | 5 | 73.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe491-il | 1,000,000 | 9 | 88 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe491-il | 1,000,000 | 5 | 86.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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