GOE 648 AIRFOIL (goe648-il)
GOE 648 AIRFOIL - Gottingen 648 airfoil
| Details | Dat file | Parser | |
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(goe648-il) GOE 648 AIRFOIL Gottingen 648 airfoil Max thickness 15.2% at 29.4% chord. Max camber 3.9% at 39.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 648 AIRFOIL
18. 17.
0.0000000 0.0000000
0.0055500 0.0236700
0.0106800 0.0330900
0.0224000 0.0473200
0.0464000 0.0655500
0.0706400 0.0793800
0.0950700 0.0897300
0.1443100 0.1034400
0.1938900 0.1111600
0.2937000 0.1146500
0.3938600 0.1116600
0.4943500 0.1026900
0.5950900 0.0892300
0.6960300 0.0722800
0.7971800 0.0513400
0.8984600 0.0279200
0.9491900 0.0147100
1.0000000 0.0000000
0.0000000 0.0000000
0.0133700 -.0157600
0.0262200 -.0220600
0.0516100 -.0291600
0.0768000 -.0327800
0.1019500 -.0353900
0.1521000 -.0381300
0.2021400 -.0388800
0.3020300 -.0368900
0.4018100 -.0329000
0.5014800 -.0269200
0.6011000 -.0199400
0.7007400 -.0134600
0.8003800 -.0069800
0.9001600 -.0029900
0.9501000 -.0017400
1.0000000 0.0000000
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Polars for GOE 648 AIRFOIL (goe648-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe648-il | 50,000 | 9 | 22.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 50,000 | 5 | 30.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe648-il | 100,000 | 9 | 43.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 100,000 | 5 | 44.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe648-il | 200,000 | 9 | 57.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 200,000 | 5 | 57.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe648-il | 500,000 | 9 | 79.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 500,000 | 5 | 80.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe648-il | 1,000,000 | 9 | 104.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 1,000,000 | 5 | 101.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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