GOE 365 AIRFOIL (goe365-il)
GOE 365 AIRFOIL - Gottingen 365 airfoil
| Details | Dat file | Parser | |
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(goe365-il) GOE 365 AIRFOIL Gottingen 365 airfoil Max thickness 11.7% at 29.9% chord. Max camber 5.1% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 365 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0122200 0.0266300
0.0245900 0.0387600
0.0493900 0.0580200
0.0742600 0.0702800
0.0991500 0.0805400
0.1490200 0.0935600
0.1989300 0.1015900
0.2988500 0.1096400
0.3988500 0.1091900
0.4989200 0.1027400
0.5990500 0.0902900
0.6992500 0.0713400
0.7994700 0.0503900
0.8997200 0.0269500
0.9498500 0.0144700
1.0000000 0.0000000
0.0000000 0.0000000
0.0126000 -.0093700
0.0251100 -.0102400
0.0501000 -.0099700
0.0751000 -.0097100
0.1001000 -.0094500
0.1500900 -.0089200
0.2000900 -.0084000
0.3000800 -.0073500
0.4000700 -.0063000
0.5000600 -.0052500
0.6000400 -.0042000
0.7000300 -.0031500
0.8000200 -.0021000
0.9000100 -.0010500
0.9500100 -.0005200
1.0000000 0.0000000
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Polars for GOE 365 AIRFOIL (goe365-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe365-il | 50,000 | 9 | 27.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe365-il | 50,000 | 5 | 34.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe365-il | 100,000 | 9 | 55.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe365-il | 100,000 | 5 | 55.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe365-il | 200,000 | 9 | 79.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe365-il | 200,000 | 5 | 73.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe365-il | 500,000 | 9 | 107.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe365-il | 500,000 | 5 | 90.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe365-il | 1,000,000 | 9 | 120.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe365-il | 1,000,000 | 5 | 99.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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