GOE 424 AIRFOIL (goe424-il)
GOE 424 AIRFOIL - Gottingen 424 airfoil
| Details | Dat file | Parser | |
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(goe424-il) GOE 424 AIRFOIL Gottingen 424 airfoil Max thickness 19.9% at 38.5% chord. Max camber 4.8% at 38.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 424 AIRFOIL
17. 17.
0.0000200 0.0000000
0.0097500 0.0279600
0.0208000 0.0425600
0.0436100 0.0646200
0.0668600 0.0823300
0.0905200 0.0957800
0.1384700 0.1164300
0.1870800 0.1304500
0.2855200 0.1461200
0.3853900 0.1474300
0.4866400 0.1347700
0.5885800 0.1151800
0.6908000 0.0928200
0.7934300 0.0663100
0.8964400 0.0359300
0.9481800 0.0183600
1.0000000 0.0008000
0.0000200 0.0000000
0.0142600 -.0164900
0.0272200 -.0221000
0.0527200 -.0277700
0.0783600 -.0336300
0.1038200 -.0383000
0.1545600 -.0457700
0.2049200 -.0493700
0.3053300 -.0535100
0.4051100 -.0514100
0.5045900 -.0461400
0.6038300 -.0385000
0.7029600 -.0297700
0.8020300 -.0204400
0.9010600 -.0106200
0.9505700 -.0057000
1.0000000 -.0008000
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Similar airfoils
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Polars for GOE 424 AIRFOIL (goe424-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe424-il | 50,000 | 9 | 3.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe424-il | 50,000 | 5 | 16.2 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe424-il | 100,000 | 9 | 22.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe424-il | 100,000 | 5 | 37.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe424-il | 200,000 | 9 | 59 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe424-il | 200,000 | 5 | 63.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe424-il | 500,000 | 9 | 96.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe424-il | 500,000 | 5 | 93.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe424-il | 1,000,000 | 9 | 124.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe424-il | 1,000,000 | 5 | 117.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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