GOE 559 AIRFOIL (goe559-il)
GOE 559 AIRFOIL - Gottingen 559 airfoil
| Details | Dat file | Parser | |
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(goe559-il) GOE 559 AIRFOIL Gottingen 559 airfoil Max thickness 11.2% at 30% chord. Max camber 3.4% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 559 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0055000
0.0250000 0.0115000
0.0500000 0.0230000
0.0750000 0.0340000
0.1000000 0.0445000
0.1500000 0.0625000
0.2000000 0.0760000
0.3000000 0.0900000
0.4000000 0.0885000
0.5000000 0.0790000
0.6000000 0.0665000
0.7000000 0.0515000
0.8000000 0.0365000
0.9000000 0.0190000
0.9500000 0.0100000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0015000
0.0250000 -.0030000
0.0500000 -.0060000
0.0750000 -.0085000
0.1000000 -.0110000
0.1500000 -.0155000
0.2000000 -.0185000
0.3000000 -.0215000
0.4000000 -.0210000
0.5000000 -.0185000
0.6000000 -.0155000
0.7000000 -.0120000
0.8000000 -.0085000
0.9000000 -.0045000
0.9500000 -.0025000
1.0000000 0.0000000
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Polars for GOE 559 AIRFOIL (goe559-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe559-il | 50,000 | 9 | 30.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 50,000 | 5 | 28.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe559-il | 100,000 | 9 | 40.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 100,000 | 5 | 38.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe559-il | 200,000 | 9 | 50.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 200,000 | 5 | 50 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe559-il | 500,000 | 9 | 66.3 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 500,000 | 5 | 64.2 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe559-il | 1,000,000 | 9 | 76.8 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 1,000,000 | 5 | 74.2 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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