GOE 775 AIRFOIL (goe775-il)
GOE 775 AIRFOIL - Gottingen 775 airfoil
| Details | Dat file | Parser | |
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(goe775-il) GOE 775 AIRFOIL Gottingen 775 airfoil Max thickness 21% at 30% chord. Max camber 0% at 1.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 775 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0332300
0.0250000 0.0458500
0.0500000 0.0623100
0.0750000 0.0736600
0.1000000 0.0820200
0.1500000 0.0938300
0.2000000 0.1007400
0.3000000 0.1056600
0.4000000 0.1023800
0.5000000 0.0938000
0.6000000 0.0811200
0.7000000 0.0657400
0.8000000 0.0483600
0.9000000 0.0272800
0.9500000 0.0162900
1.0000000 0.0044000
0.0000000 0.0000000
0.0125000 -.0331700
0.0250000 -.0457500
0.0500000 -.0620900
0.0750000 -.0733300
0.1000000 -.0815800
0.1500000 -.0931700
0.2000000 -.0998600
0.3000000 -.1043400
0.4000000 -.1006200
0.5000000 -.0916000
0.6000000 -.0784800
0.7000000 -.0626600
0.8000000 -.0448400
0.9000000 -.0233200
0.9500000 -.0121100
1.0000000 0.0000000
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Polars for GOE 775 AIRFOIL (goe775-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe775-il | 50,000 | 9 | 18.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe775-il | 50,000 | 5 | 25.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe775-il | 100,000 | 9 | 36.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe775-il | 100,000 | 5 | 35.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe775-il | 200,000 | 9 | 48.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe775-il | 200,000 | 5 | 43.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe775-il | 500,000 | 9 | 60.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe775-il | 500,000 | 5 | 56.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe775-il | 1,000,000 | 9 | 74.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe775-il | 1,000,000 | 5 | 69.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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