GOE 570 AIRFOIL (goe570-il)
GOE 570 AIRFOIL - Gottingen 570 airfoil
| Details | Dat file | Parser | |
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(goe570-il) GOE 570 AIRFOIL Gottingen 570 airfoil Max thickness 33.7% at 30% chord. Max camber 9.7% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 570 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0520000
0.0250000 0.0800000
0.0500000 0.1210000
0.0750000 0.1530000
0.1000000 0.1785000
0.1500000 0.2140000
0.2000000 0.2395000
0.3000000 0.2635000
0.4000000 0.2625000
0.5000000 0.2445000
0.6000000 0.2140000
0.7000000 0.1720000
0.8000000 0.1230000
0.9000000 0.0670000
0.9500000 0.0375000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0225000
0.0250000 -.0365000
0.0500000 -.0490000
0.0750000 -.0565000
0.1000000 -.0618000
0.1500000 -.0695000
0.2000000 -.0715000
0.3000000 -.0735000
0.4000000 -.0690000
0.5000000 -.0605000
0.6000000 -.0510000
0.7000000 -.0415000
0.8000000 -.0310000
0.9000000 -.0200000
0.9500000 -.0109000
1.0000000 0.0000000
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Polars for GOE 570 AIRFOIL (goe570-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe570-il | 50,000 | 9 | 0.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 50,000 | 5 | 2.5 at α=-14° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe570-il | 100,000 | 9 | 7.1 at α=-12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 100,000 | 5 | 6.3 at α=-14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe570-il | 200,000 | 9 | 7.8 at α=-14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 200,000 | 5 | 10.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe570-il | 500,000 | 9 | 23.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 500,000 | 5 | 15.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe570-il | 1,000,000 | 9 | 20.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 1,000,000 | 5 | 16.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||