GOE 562 AIRFOIL (goe562-il)
GOE 562 AIRFOIL - Gottingen 562 airfoil
| Details | Dat file | Parser | |
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(goe562-il) GOE 562 AIRFOIL Gottingen 562 airfoil Max thickness 14.1% at 30% chord. Max camber 6.3% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 562 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124100 0.0245400
0.0248700 0.0375900
0.0498000 0.0566700
0.0747400 0.0732600
0.0996900 0.0873500
0.1496100 0.1100200
0.1995700 0.1222000
0.2995300 0.1330500
0.3995500 0.1299000
0.4995900 0.1172500
0.5996500 0.0991000
0.6997200 0.0789500
0.7998000 0.0568000
0.8998800 0.0336500
0.9499300 0.0208200
1.0000000 0.0000000
0.0000000 0.0000000
0.0125400 -.0104600
0.0250400 -.0124100
0.0500400 -.0123200
0.0750400 -.0122400
0.1000400 -.0121500
0.1500400 -.0109700
0.2000400 -.0103000
0.3000300 -.0079500
0.4000200 -.0066000
0.5000200 -.0062500
0.6000200 -.0059000
0.7000200 -.0060500
0.8000200 -.0067000
0.9000300 -.0073500
0.9500300 -.0061700
1.0000000 0.0000000
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Polars for GOE 562 AIRFOIL (goe562-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe562-il | 50,000 | 9 | 9.2 at α=-4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 50,000 | 5 | 25.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 100,000 | 9 | 40.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 100,000 | 5 | 50 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 200,000 | 9 | 70.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 200,000 | 5 | 70.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 500,000 | 9 | 101.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 500,000 | 5 | 96.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 1,000,000 | 9 | 126.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 1,000,000 | 5 | 115.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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