GOE 443 AIRFOIL (goe443-il)
GOE 443 AIRFOIL - Gottingen 443 airfoil
| Details | Dat file | Parser | |
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(goe443-il) GOE 443 AIRFOIL Gottingen 443 airfoil Max thickness 5% at 30% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 443 AIRFOIL
15. 15.
0.0000000 0.0000000
0.0125000 0.0060000
0.0250000 0.0085000
0.0500000 0.0115000
0.0750000 0.0140000
0.1000000 0.0160000
0.2000000 0.0215000
0.3000000 0.0250000
0.4000000 0.0250000
0.5000000 0.0235000
0.6000000 0.0205000
0.7000000 0.0165000
0.8000000 0.0115000
0.9000000 0.0065000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0060000
0.0250000 -.0085000
0.0500000 -.0115000
0.0750000 -.0140000
0.1000000 -.0160000
0.2000000 -.0215000
0.3000000 -.0250000
0.4000000 -.0250000
0.5000000 -.0235000
0.6000000 -.0205000
0.7000000 -.0165000
0.8000000 -.0115000
0.9000000 -.0065000
1.0000000 0.0000000
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Polars for GOE 443 AIRFOIL (goe443-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe443-il | 50,000 | 9 | 16.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe443-il | 50,000 | 5 | 16 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe443-il | 100,000 | 9 | 20.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe443-il | 100,000 | 5 | 26.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe443-il | 200,000 | 9 | 34 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe443-il | 200,000 | 5 | 32.2 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe443-il | 500,000 | 9 | 44.5 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe443-il | 500,000 | 5 | 32 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe443-il | 1,000,000 | 9 | 43.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe443-il | 1,000,000 | 5 | 60.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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