GOE 522 AIRFOIL (goe522-il)
GOE 522 AIRFOIL - Gottingen 522 airfoil
| Details | Dat file | Parser | |
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(goe522-il) GOE 522 AIRFOIL Gottingen 522 airfoil Max thickness 21.8% at 28.6% chord. Max camber 5.2% at 48.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 522 AIRFOIL
17. 17.
0.0000100 0.0000000
0.0095100 0.0343300
0.0206100 0.0503000
0.0435100 0.0743100
0.0669800 0.0918600
0.0906600 0.1069300
0.1386700 0.1296300
0.1875100 0.1429000
0.2863100 0.1565500
0.3863800 0.1558000
0.4873500 0.1446400
0.5888000 0.1280200
0.6908700 0.1044500
0.7934500 0.0749300
0.8965500 0.0394500
0.9482500 0.0199700
1.0000000 0.0000000
0.0000100 0.0000000
0.0151500 -.0301700
0.0283000 -.0375200
0.0543700 -.0497400
0.0799600 -.0565000
0.1053300 -.0607800
0.1556900 -.0648800
0.2058300 -.0664900
0.3053300 -.0607800
0.4044400 -.0506100
0.5033700 -.0384600
0.6023100 -.0263000
0.7013700 -.0156300
0.8006099 -.0069500
0.9000700 -.0007400
0.9499900 0.0001200
1.0000000 0.0000000
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Polars for GOE 522 AIRFOIL (goe522-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe522-il | 50,000 | 9 | 3 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe522-il | 50,000 | 5 | 9.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe522-il | 100,000 | 9 | 32.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe522-il | 100,000 | 5 | 37.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe522-il | 200,000 | 9 | 57.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe522-il | 200,000 | 5 | 51.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe522-il | 500,000 | 9 | 73.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe522-il | 500,000 | 5 | 63.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe522-il | 1,000,000 | 9 | 89.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe522-il | 1,000,000 | 5 | 70.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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