GOE 458 AIRFOIL (goe458-il)
GOE 458 AIRFOIL - Gottingen 458 airfoil
| Details | Dat file | Parser | |
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(goe458-il) GOE 458 AIRFOIL Gottingen 458 airfoil Max thickness 7.2% at 29.9% chord. Max camber 5.2% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 458 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124100 0.0125900
0.0248400 0.0206900
0.0497400 0.0343700
0.0746600 0.0450600
0.0996000 0.0537500
0.1495100 0.0656200
0.1994500 0.0735000
0.2993700 0.0837500
0.3993500 0.0870000
0.4993800 0.0827500
0.5994500 0.0735000
0.6995400 0.0607500
0.7996700 0.0435000
0.8998300 0.0232500
0.9499100 0.0121200
1.0000000 0.0000000
0.0000000 0.0000000
0.0125300 -.0045100
0.0250400 -.0063100
0.0500600 -.0076200
0.0750600 -.0079400
0.1000500 -.0067500
0.1499900 -.0019300
0.1999800 0.0030000
0.2999100 0.0117500
0.3998700 0.0170000
0.4998600 0.0187500
0.5998600 0.0185000
0.6998700 0.0167500
0.7999099 0.0125000
0.8999600 0.0057500
0.9499800 0.0031200
1.0000000 0.0000000
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Polars for GOE 458 AIRFOIL (goe458-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe458-il | 50,000 | 9 | 42.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe458-il | 50,000 | 5 | 42.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe458-il | 100,000 | 9 | 65.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe458-il | 100,000 | 5 | 64.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe458-il | 200,000 | 9 | 87.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe458-il | 200,000 | 5 | 86.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe458-il | 500,000 | 9 | 117.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe458-il | 500,000 | 5 | 115.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe458-il | 1,000,000 | 9 | 140.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe458-il | 1,000,000 | 5 | 136.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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