GOE 362 AIRFOIL (goe362-il)
GOE 362 AIRFOIL - Gottingen 362 airfoil
| Details | Dat file | Parser | |
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(goe362-il) GOE 362 AIRFOIL Gottingen 362 airfoil Max thickness 6.6% at 20% chord. Max camber 5.3% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 362 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0205700
0.0250000 0.0296500
0.0500000 0.0418000
0.0750000 0.0509500
0.1000000 0.0586000
0.1500000 0.0699000
0.2000000 0.0772000
0.3000000 0.0833000
0.4000000 0.0814000
0.5000000 0.0755000
0.6000000 0.0651000
0.7000000 0.0522000
0.8000000 0.0368000
0.9000000 0.0194000
0.9500000 0.0097000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0049300
0.0250000 -.0058500
0.0500000 -.0052000
0.0750000 -.0030500
0.1000000 0.0001000
0.1500000 0.0054000
0.2000000 0.0112000
0.3000000 0.0193000
0.4000000 0.0244000
0.5000000 0.0265000
0.6000000 0.0256000
0.7000000 0.0212000
0.8000000 0.0168000
0.9000000 0.0084000
0.9500000 0.0037000
1.0000000 0.0000000
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Similar airfoils
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Polars for GOE 362 AIRFOIL (goe362-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe362-il | 50,000 | 9 | 37.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 50,000 | 5 | 43.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 100,000 | 9 | 58.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 100,000 | 5 | 63.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 200,000 | 9 | 79.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 200,000 | 5 | 81.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 500,000 | 9 | 109.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 500,000 | 5 | 108.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 1,000,000 | 9 | 131.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 1,000,000 | 5 | 127.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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