GOE 370 AIRFOIL (goe370-il)
GOE 370 AIRFOIL - Gottingen 370 airfoil
| Details | Dat file | Parser | |
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(goe370-il) GOE 370 AIRFOIL Gottingen 370 airfoil Max thickness 4.7% at 20% chord. Max camber 5.7% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 370 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124300 0.0120700
0.0249000 0.0186400
0.0498400 0.0297700
0.0747900 0.0389100
0.0997400 0.0465500
0.1496800 0.0588200
0.1996300 0.0671000
0.2995800 0.0766500
0.3995600 0.0797000
0.4995800 0.0757500
0.5996300 0.0678000
0.6997000 0.0543500
0.7997900 0.0384000
0.8998800 0.0209500
0.9499400 0.0112200
1.0000000 0.0000000
0.0000000 0.0000000
0.0125300 -.0054300
0.0250300 -.0053600
0.0500200 -.0032200
0.0750000 0.0004100
0.0999700 0.0045500
0.1499200 0.0138200
0.1998900 0.0206000
0.2998300 0.0306500
0.3998100 0.0352000
0.4998200 0.0332500
0.5998500 0.0278000
0.6998800 0.0213500
0.7999300 0.0129000
0.8999700 0.0049500
0.9499900 0.0022200
1.0000000 0.0000000
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Polars for GOE 370 AIRFOIL (goe370-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe370-il | 50,000 | 9 | 45.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe370-il | 50,000 | 5 | 44.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe370-il | 100,000 | 9 | 67.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe370-il | 100,000 | 5 | 67.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe370-il | 200,000 | 9 | 92 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe370-il | 200,000 | 5 | 92.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe370-il | 500,000 | 9 | 128.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe370-il | 500,000 | 5 | 121.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe370-il | 1,000,000 | 9 | 154.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe370-il | 1,000,000 | 5 | 119.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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