GOE 526 AIRFOIL (goe526-il)
GOE 526 AIRFOIL - Gottingen 526 airfoil
| Details | Dat file | Parser | |
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(goe526-il) GOE 526 AIRFOIL Gottingen 526 airfoil Max thickness 12.3% at 29.7% chord. Max camber 4.1% at 39.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 526 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0117400 0.0268300
0.0239300 0.0376800
0.0485100 0.0523800
0.0732000 0.0630900
0.0979500 0.0717900
0.1476100 0.0839100
0.1973500 0.0931200
0.2971100 0.1014700
0.3971300 0.1008200
0.4972900 0.0951700
0.5976200 0.0835300
0.6981100 0.0664000
0.7986799 0.0462600
0.8993100 0.0241300
0.9496601 0.0120700
1.0000000 0.0000000
0.0000000 0.0000000
0.0130000 -.0176300
0.0256600 -.0232700
0.0508000 -.0280500
0.0758500 -.0298400
0.1008600 -.0301300
0.1508000 -.0282000
0.2007300 -.0257800
0.3006100 -.0214300
0.4005200 -.0180900
0.5004300 -.0152400
0.6003700 -.0128900
0.7003601 -.0125400
0.8002900 -.0101900
0.9001700 -.0058500
0.9500800 -.0029200
1.0000000 0.0000000
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Similar airfoils
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Polars for GOE 526 AIRFOIL (goe526-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe526-il | 50,000 | 9 | 24.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe526-il | 50,000 | 5 | 33.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe526-il | 100,000 | 9 | 52.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe526-il | 100,000 | 5 | 52.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe526-il | 200,000 | 9 | 73.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe526-il | 200,000 | 5 | 69.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe526-il | 500,000 | 9 | 98.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe526-il | 500,000 | 5 | 91.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe526-il | 1,000,000 | 9 | 119.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe526-il | 1,000,000 | 5 | 107.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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