GOE 523 AIRFOIL (goe523-il)
GOE 523 AIRFOIL - Gottingen 523 airfoil
| Details | Dat file | Parser | |
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(goe523-il) GOE 523 AIRFOIL Gottingen 523 airfoil Max thickness 16.5% at 29.7% chord. Max camber 9.7% at 49.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 523 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0117600 0.0372400
0.0239000 0.0549800
0.0484000 0.0799700
0.0730400 0.0979600
0.0977200 0.1139500
0.1472300 0.1384400
0.1969200 0.1539400
0.2966100 0.1694300
0.3965900 0.1704300
0.4967600 0.1619400
0.5971000 0.1449400
0.6975600 0.1219500
0.7981900 0.0904600
0.8990000 0.0499800
0.9494800 0.0259900
1.0000000 0.0000000
0.0000000 0.0000000
0.0127600 -.0132400
0.0253300 -.0164900
0.0503700 -.0184900
0.0753700 -.0184900
0.1003500 -.0174900
0.1502600 -.0129900
0.2001600 -.0080000
0.2999000 0.0050000
0.3996300 0.0184900
0.4993500 0.0324900
0.5990900 0.0454800
0.6989400 0.0529800
0.7990300 0.0484800
0.8993900 0.0304900
0.9496601 0.0169900
1.0000000 0.0000000
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Polars for GOE 523 AIRFOIL (goe523-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe523-il | 50,000 | 9 | 5.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe523-il | 50,000 | 5 | 20.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe523-il | 100,000 | 9 | 48.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe523-il | 100,000 | 5 | 50.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe523-il | 200,000 | 9 | 74.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe523-il | 200,000 | 5 | 71.5 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe523-il | 500,000 | 9 | 102.1 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe523-il | 500,000 | 5 | 90.6 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe523-il | 1,000,000 | 9 | 120.6 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe523-il | 1,000,000 | 5 | 104.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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