GOE 123 AIRFOIL (goe123-il)
GOE 123 AIRFOIL - Gottingen 123 airfoil
| Details | Dat file | Parser | |
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(goe123-il) GOE 123 AIRFOIL Gottingen 123 airfoil Max thickness 5.4% at 25% chord. Max camber 5.7% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 123 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0181300
0.0250000 0.0262500
0.0500000 0.0395000
0.0750000 0.0487500
0.1000000 0.0570000
0.1500000 0.0685000
0.2000000 0.0760000
0.2500000 0.0805000
0.3000000 0.0830000
0.4000000 0.0840000
0.5000000 0.0800000
0.6000000 0.0720000
0.7000000 0.0590000
0.8000000 0.0420000
0.9000000 0.0220000
1.0000000 0.0020000
0.0000000 0.0000000
0.0125000 -.0088700
0.0250000 -.0077500
0.0500000 -.0035000
0.0750000 0.0017500
0.1000000 0.0070000
0.1500000 0.0175000
0.2000000 0.0230000
0.2500000 0.0265000
0.3000000 0.0290000
0.4000000 0.0300000
0.5000000 0.0270000
0.6000000 0.0220000
0.7000000 0.0170000
0.8000000 0.0110000
0.9000000 0.0060000
1.0000000 0.0000000
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Polars for GOE 123 AIRFOIL (goe123-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe123-il | 50,000 | 9 | 40.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe123-il | 50,000 | 5 | 45.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe123-il | 100,000 | 9 | 65.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe123-il | 100,000 | 5 | 66.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe123-il | 200,000 | 9 | 92 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe123-il | 200,000 | 5 | 85 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe123-il | 500,000 | 9 | 118.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe123-il | 500,000 | 5 | 102.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe123-il | 1,000,000 | 9 | 129.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe123-il | 1,000,000 | 5 | 110.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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