GOE 573 AIRFOIL (goe573-il)
GOE 573 AIRFOIL - Gottingen 573 airfoil
| Details | Dat file | Parser | |
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(goe573-il) GOE 573 AIRFOIL Gottingen 573 airfoil Max thickness 14.1% at 29.9% chord. Max camber 6.5% at 29.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 573 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123900 0.0245600
0.0248300 0.0371100
0.0497400 0.0572200
0.0746700 0.0738400
0.0996100 0.0874500
0.1495100 0.1087700
0.1994500 0.1224000
0.2993900 0.1353500
0.3994100 0.1313000
0.4994700 0.1182500
0.5995500 0.0997000
0.6996500 0.0786500
0.7997500 0.0556000
0.8998600 0.0315500
0.9499199 0.0187700
1.0000000 0.0000000
0.0000000 0.0000000
0.0125500 -.0104400
0.0250600 -.0123900
0.0500600 -.0122700
0.0750500 -.0116600
0.1000500 -.0105500
0.1500400 -.0083200
0.2000300 -.0076000
0.3000300 -.0056500
0.4000200 -.0042000
0.5000200 -.0047500
0.6000300 -.0058000
0.7000300 -.0068500
0.8000400 -.0079000
0.9000400 -.0079500
0.9500400 -.0047500
1.0000000 0.0000000
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Polars for GOE 573 AIRFOIL (goe573-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe573-il | 50,000 | 9 | 11.6 at α=-4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe573-il | 50,000 | 5 | 24.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe573-il | 100,000 | 9 | 34.4 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe573-il | 100,000 | 5 | 47.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe573-il | 200,000 | 9 | 64.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe573-il | 200,000 | 5 | 69.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe573-il | 500,000 | 9 | 99.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe573-il | 500,000 | 5 | 100 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe573-il | 1,000,000 | 9 | 130.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe573-il | 1,000,000 | 5 | 127.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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