GOE 532 AIRFOIL (goe532-il)
GOE 532 AIRFOIL - Gottingen 532 airfoil
| Details | Dat file | Parser | |
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(goe532-il) GOE 532 AIRFOIL Gottingen 532 airfoil Max thickness 12.5% at 30% chord. Max camber 4.8% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 532 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0342900
0.0250000 0.0465900
0.0500000 0.0621800
0.0765000 0.0738000
0.1000000 0.0833500
0.1500000 0.0950200
0.2000000 0.1027000
0.3000000 0.1100500
0.4000000 0.1054000
0.5000000 0.0942500
0.6000000 0.0796000
0.7000000 0.0629500
0.8000000 0.0433000
0.9000000 0.0226500
0.9500000 0.0118300
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0127100
0.0250000 -.0159100
0.0500000 -.0183200
0.0765000 -.0197000
0.1000000 -.0206500
0.1500000 -.0209800
0.2000000 -.0198000
0.3000000 -.0149500
0.4000000 -.0086000
0.5000000 -.0022500
0.6000000 0.0031000
0.7000000 0.0069500
0.8000000 0.0078000
0.9000000 0.0046500
0.9500000 0.0023300
1.0000000 0.0000000
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Polars for GOE 532 AIRFOIL (goe532-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe532-il | 50,000 | 9 | 17.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe532-il | 50,000 | 5 | 34.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe532-il | 100,000 | 9 | 53.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe532-il | 100,000 | 5 | 56 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe532-il | 200,000 | 9 | 76.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe532-il | 200,000 | 5 | 73.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe532-il | 500,000 | 9 | 101.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe532-il | 500,000 | 5 | 89.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe532-il | 1,000,000 | 9 | 115.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe532-il | 1,000,000 | 5 | 102.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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