GOE 257 AIRFOIL (goe257-il)
GOE 257 AIRFOIL - Gottingen 257 airfoil
| Details | Dat file | Parser | |
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(goe257-il) GOE 257 AIRFOIL Gottingen 257 airfoil Max thickness 8.8% at 30% chord. Max camber 4.1% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 257 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124500 0.0161400
0.0249200 0.0252800
0.0498800 0.0376600
0.0748400 0.0484400
0.0998200 0.0575200
0.1497800 0.0694800
0.1997500 0.0766400
0.2997300 0.0849600
0.3997300 0.0836800
0.4997500 0.0776000
0.5997900 0.0661200
0.6998300 0.0526400
0.7998700 0.0394600
0.8999299 0.0232800
0.9499500 0.0148400
1.0000000 0.0064000
0.0000000 0.0000000
0.0125300 -.0095600
0.0250300 -.0095200
0.0500300 -.0089400
0.0750300 -.0082600
0.1000200 -.0071800
0.1500200 -.0059200
0.2000200 -.0046600
0.3000100 -.0033400
0.4000100 -.0025200
0.5000100 -.0027000
0.6000100 -.0023800
0.7000100 -.0030600
0.8000100 -.0038400
0.9000200 -.0051200
0.9500200 -.0065600
1.0000000 -.0064000
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Polars for GOE 257 AIRFOIL (goe257-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe257-il | 50,000 | 9 | 38.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe257-il | 50,000 | 5 | 39.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe257-il | 100,000 | 9 | 56.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe257-il | 100,000 | 5 | 57.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe257-il | 200,000 | 9 | 74.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe257-il | 200,000 | 5 | 72.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe257-il | 500,000 | 9 | 96 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe257-il | 500,000 | 5 | 88.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe257-il | 1,000,000 | 9 | 109.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe257-il | 1,000,000 | 5 | 92.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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