GOE 675 AIRFOIL (goe675-il)
GOE 675 AIRFOIL - Gottingen 675 airfoil
| Details | Dat file | Parser | |
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(goe675-il) GOE 675 AIRFOIL Gottingen 675 airfoil Max thickness 14.9% at 29.5% chord. Max camber 5.9% at 39.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 675 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0114100 0.0314000
0.0235100 0.0428200
0.0478600 0.0616600
0.0723600 0.0760100
0.0969500 0.0878700
0.1463300 0.1055900
0.1959100 0.1178100
0.2954900 0.1297700
0.3954700 0.1302400
0.4956700 0.1247200
0.5961000 0.1122100
0.6967800 0.0927100
0.7977000 0.0662200
0.8987900 0.0347300
0.9493600 0.0184900
1.0000000 0.0017500
0.0000000 0.0000000
0.0132000 -.0200400
0.0259100 -.0261000
0.0511200 -.0322200
0.0761600 -.0333500
0.1011500 -.0329900
0.1510500 -.0302500
0.2009400 -.0270200
0.3006600 -.0190500
0.4004400 -.0125800
0.5002600 -.0076200
0.6001400 -.0041400
0.7000800 -.0021700
0.8000400 -.0012000
0.9000400 -.0012200
0.9500500 -.0014900
1.0000000 -.0017500
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Polars for GOE 675 AIRFOIL (goe675-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe675-il | 50,000 | 9 | 8.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 50,000 | 5 | 28.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 100,000 | 9 | 51.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 100,000 | 5 | 52.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 200,000 | 9 | 75.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 200,000 | 5 | 69.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 500,000 | 9 | 104.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 500,000 | 5 | 90.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 1,000,000 | 9 | 117.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 1,000,000 | 5 | 111.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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