GOE 574 AIRFOIL (goe574-il)
GOE 574 AIRFOIL - Gottingen 574 airfoil
| Details | Dat file | Parser | |
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(goe574-il) GOE 574 AIRFOIL Gottingen 574 airfoil Max thickness 10.3% at 30% chord. Max camber 4.9% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 574 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124200 0.0150600
0.0248800 0.0241200
0.0498100 0.0387500
0.0747500 0.0508700
0.0996900 0.0620000
0.1496100 0.0777500
0.1995600 0.0885000
0.2995000 0.1005000
0.3995100 0.0990000
0.4995400 0.0915000
0.5996000 0.0800000
0.6996700 0.0655000
0.7997600 0.0490000
0.8998400 0.0315000
0.9499000 0.0197500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125400 -.0079400
0.0250400 -.0088700
0.0500500 -.0097500
0.0750500 -.0096200
0.1000500 -.0090000
0.1500300 -.0067500
0.2000300 -.0050000
0.3000100 -.0020000
0.4000000 -.0005000
0.5000000 0.0000000
0.6000100 -.0010000
0.7000100 -.0020000
0.8000200 -.0035000
0.9000200 -.0045000
0.9500300 -.0027800
1.0000000 0.0000000
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Polars for GOE 574 AIRFOIL (goe574-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe574-il | 50,000 | 9 | 34.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe574-il | 50,000 | 5 | 35.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe574-il | 100,000 | 9 | 56 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe574-il | 100,000 | 5 | 55.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe574-il | 200,000 | 9 | 74.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe574-il | 200,000 | 5 | 73.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe574-il | 500,000 | 9 | 100 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe574-il | 500,000 | 5 | 97.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe574-il | 1,000,000 | 9 | 121.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe574-il | 1,000,000 | 5 | 118.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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