GOE 513 AIRFOIL (goe513-il)
GOE 513 AIRFOIL - Gottingen 513 airfoil
| Details | Dat file | Parser | |
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(goe513-il) GOE 513 AIRFOIL Gottingen 513 airfoil Max thickness 16.6% at 29.8% chord. Max camber 5.2% at 39.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 513 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0119400 0.0322100
0.0241500 0.0484200
0.0487500 0.0713500
0.0734600 0.0882900
0.0982300 0.1012200
0.1479200 0.1185900
0.1977600 0.1279600
0.2976300 0.1352100
0.3977000 0.1314600
0.4978900 0.1207100
0.5981200 0.1074700
0.6984600 0.0877200
0.7988600 0.0649800
0.8993700 0.0357400
0.9496900 0.0176200
1.0000000 0.0000000
0.0000000 0.0000000
0.0128000 -.0172800
0.0253900 -.0225600
0.0505000 -.0286200
0.0755800 -.0331800
0.1006300 -.0362400
0.1506900 -.0393600
0.2006600 -.0379900
0.3005400 -.0307400
0.4004700 -.0269900
0.5004900 -.0282400
0.6005300 -.0304900
0.7005200 -.0297400
0.8004300 -.0244900
0.9002900 -.0167400
0.9501800 -.0103700
1.0000000 0.0000000
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Similar airfoils
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Polars for GOE 513 AIRFOIL (goe513-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe513-il | 50,000 | 9 | 10.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe513-il | 50,000 | 5 | 28.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe513-il | 100,000 | 9 | 44.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe513-il | 100,000 | 5 | 43 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe513-il | 200,000 | 9 | 58.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe513-il | 200,000 | 5 | 54.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe513-il | 500,000 | 9 | 75.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe513-il | 500,000 | 5 | 66.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe513-il | 1,000,000 | 9 | 86.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe513-il | 1,000,000 | 5 | 76.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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