GOE 512 AIRFOIL (goe512-il)
GOE 512 AIRFOIL - Gottingen 512 airfoil
| Details | Dat file | Parser | |
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(goe512-il) GOE 512 AIRFOIL Gottingen 512 airfoil Max thickness 13.9% at 19.9% chord. Max camber 5.6% at 29.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 512 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0121500 0.0301400
0.0244900 0.0447800
0.0492400 0.0660700
0.0740600 0.0813500
0.0989300 0.0926400
0.1487500 0.1087100
0.1986500 0.1172800
0.2985700 0.1244300
0.3986100 0.1210800
0.4987000 0.1127400
0.5988600 0.0988900
0.6990600 0.0820400
0.7993000 0.0606900
0.8996100 0.0343500
0.9497899 0.0179200
1.0000000 0.0000000
0.0000000 0.0000000
0.0126200 -.0103500
0.0251700 -.0147100
0.0502200 -.0189200
0.0752400 -.0211300
0.1002600 -.0228500
0.1502700 -.0232700
0.2002500 -.0217000
0.3001400 -.0120500
0.4001300 -.0109000
0.5001400 -.0122500
0.6001700 -.0151000
0.7001899 -.0169500
0.8001800 -.0153000
0.9001200 -.0106500
0.9500700 -.0060700
1.0000000 0.0000000
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Similar airfoils
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Polars for GOE 512 AIRFOIL (goe512-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe512-il | 50,000 | 9 | 19.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe512-il | 50,000 | 5 | 31.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe512-il | 100,000 | 9 | 48.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe512-il | 100,000 | 5 | 47.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe512-il | 200,000 | 9 | 64.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe512-il | 200,000 | 5 | 60.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe512-il | 500,000 | 9 | 83.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe512-il | 500,000 | 5 | 74.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe512-il | 1,000,000 | 9 | 95.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe512-il | 1,000,000 | 5 | 88.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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