GOE 646 AIRFOIL (goe646-il)
GOE 646 AIRFOIL - Gottingen 646 airfoil
| Details | Dat file | Parser | |
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(goe646-il) GOE 646 AIRFOIL Gottingen 646 airfoil Max thickness 18.3% at 29% chord. Max camber 4.5% at 49% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 646 AIRFOIL
17. 17.
0.0000100 0.0000000
0.0101500 0.0302900
0.0215200 0.0446800
0.0450500 0.0635100
0.0689700 0.0773800
0.0930500 0.0892600
0.1417400 0.1060500
0.1908500 0.1173800
0.2899700 0.1286200
0.3898300 0.1304100
0.4904700 0.1222600
0.5916100 0.1076400
0.6931000 0.0885600
0.7950500 0.0635100
0.8973100 0.0344900
0.9485199 0.0189800
1.0000000 0.0000000
0.0000100 0.0000000
0.0144100 -.0243800
0.0276100 -.0333500
0.0534700 -.0443300
0.0789700 -.0508400
0.1043300 -.0553600
0.1546800 -.0599300
0.2047300 -.0605300
0.3042000 -.0537700
0.4033200 -.0425400
0.5024500 -.0313100
0.6015300 -.0195800
0.7006900 -.0088500
0.8002000 -.0025800
0.8999500 0.0007000
0.9499500 0.0006000
1.0000000 0.0000000
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Polars for GOE 646 AIRFOIL (goe646-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe646-il | 50,000 | 9 | 5.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 50,000 | 5 | 18.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 100,000 | 9 | 43.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 100,000 | 5 | 46.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 200,000 | 9 | 68.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 200,000 | 5 | 65.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 500,000 | 9 | 95.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 500,000 | 5 | 77.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 1,000,000 | 9 | 105.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 1,000,000 | 5 | 85.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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