GOE 567 AIRFOIL (goe567-il)
GOE 567 AIRFOIL - Gottingen 567 airfoil
| Details | Dat file | Parser | |
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(goe567-il) GOE 567 AIRFOIL Gottingen 567 airfoil Max thickness 14.8% at 29.5% chord. Max camber 5.3% at 49.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 567 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0114200 0.0235300
0.0233600 0.0355700
0.0476500 0.0511900
0.0720200 0.0648100
0.0965800 0.0744400
0.1458100 0.0912100
0.1952400 0.1034800
0.2945900 0.1175500
0.3945000 0.1196500
0.4948400 0.1122600
0.5955000 0.0978900
0.6964300 0.0775400
0.7974800 0.0546800
0.8986500 0.0293400
0.9493000 0.0151700
1.0000000 0.0000000
0.0000000 0.0000000
0.0133000 -.0173900
0.0261400 -.0248000
0.0514800 -.0321300
0.0766100 -.0349800
0.1016900 -.0368200
0.1517500 -.0380200
0.2016900 -.0367200
0.3013600 -.0296400
0.4008500 -.0185600
0.5003000 -.0064900
0.5998400 0.0035900
0.6995800 0.0091800
0.7995500 0.0097800
0.8996800 0.0068900
0.9497800 0.0046900
1.0000000 0.0000000
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Polars for GOE 567 AIRFOIL (goe567-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe567-il | 50,000 | 9 | 6.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe567-il | 50,000 | 5 | 21.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe567-il | 100,000 | 9 | 49.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe567-il | 100,000 | 5 | 56 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe567-il | 200,000 | 9 | 81 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe567-il | 200,000 | 5 | 79.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe567-il | 500,000 | 9 | 115.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe567-il | 500,000 | 5 | 95.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe567-il | 1,000,000 | 9 | 132.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe567-il | 1,000,000 | 5 | 103.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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