GOE 360 AIRFOIL (goe360-il)
GOE 360 AIRFOIL - Gottingen 360 airfoil
| Details | Dat file | Parser | |
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(goe360-il) GOE 360 AIRFOIL Gottingen 360 airfoil Max thickness 9.7% at 29.9% chord. Max camber 5.9% at 29.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 360 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123000 0.0212200
0.0247000 0.0319400
0.0495300 0.0491700
0.0744100 0.0621100
0.0993000 0.0729500
0.1491500 0.0895200
0.1990500 0.0998000
0.2989800 0.1070600
0.3990000 0.1043100
0.4990900 0.0952700
0.5992300 0.0808200
0.6993901 0.0643800
0.7995800 0.0441400
0.8997900 0.0217900
0.9498900 0.0116700
1.0000000 0.0010500
0.0000000 0.0000000
0.0126000 -.0104800
0.0250900 -.0098600
0.0500500 -.0053200
0.0750200 -.0018800
0.0999900 0.0008500
0.1499500 0.0048300
0.1999300 0.0076100
0.2999000 0.0102600
0.3998900 0.0117200
0.4999000 0.0100700
0.5999300 0.0081700
0.6999400 0.0058000
0.7999700 0.0033400
0.8999800 0.0010800
0.9500000 0.0000700
1.0000000 -.0010500
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Similar airfoils
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Polars for GOE 360 AIRFOIL (goe360-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe360-il | 50,000 | 9 | 20.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe360-il | 50,000 | 5 | 36.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe360-il | 100,000 | 9 | 51.4 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe360-il | 100,000 | 5 | 56.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe360-il | 200,000 | 9 | 73.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe360-il | 200,000 | 5 | 76.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe360-il | 500,000 | 9 | 105.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe360-il | 500,000 | 5 | 104.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe360-il | 1,000,000 | 9 | 131.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe360-il | 1,000,000 | 5 | 127.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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