GOE 508 AIRFOIL (goe508-il)
GOE 508 AIRFOIL - Gottingen 508 airfoil
| Details | Dat file | Parser | |
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(goe508-il) GOE 508 AIRFOIL Gottingen 508 airfoil Max thickness 16.5% at 30% chord. Max camber 5.6% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 508 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0310100
0.0250000 0.0475300
0.0500000 0.0680500
0.0750000 0.0840800
0.1000000 0.0961000
0.1500000 0.1136500
0.2000000 0.1242000
0.3000000 0.1363000
0.4000000 0.1374000
0.5000000 0.1275000
0.6000000 0.1101000
0.7000000 0.0862000
0.8000000 0.0583000
0.9000000 0.0294000
0.9500000 0.0144500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0209900
0.0250000 -.0269700
0.0500000 -.0319500
0.0750000 -.0344300
0.1000000 -.0349000
0.1500000 -.0343500
0.2000000 -.0328000
0.3000000 -.0287000
0.4000000 -.0246000
0.5000000 -.0205000
0.6000000 -.0164000
0.7000000 -.0123000
0.8000000 -.0082000
0.9000000 -.0041000
0.9500000 -.0020500
1.0000000 0.0000000
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Polars for GOE 508 AIRFOIL (goe508-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe508-il | 50,000 | 9 | 5.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe508-il | 50,000 | 5 | 13.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe508-il | 100,000 | 9 | 40.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe508-il | 100,000 | 5 | 43.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe508-il | 200,000 | 9 | 71.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe508-il | 200,000 | 5 | 69.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe508-il | 500,000 | 9 | 105.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe508-il | 500,000 | 5 | 97.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe508-il | 1,000,000 | 9 | 132.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe508-il | 1,000,000 | 5 | 115.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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