GOE 427 AIRFOIL (goe427-il)
GOE 427 AIRFOIL - Gottingen 427 airfoil
| Details | Dat file | Parser | |
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(goe427-il) GOE 427 AIRFOIL Gottingen 427 airfoil Max thickness 4.6% at 20% chord. Max camber 5.4% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 427 AIRFOIL
17. 17.
0.0000000 0.0045000
0.0125000 0.0190000
0.0250000 0.0250000
0.0500000 0.0360000
0.0750000 0.0440000
0.1000000 0.0510000
0.1500000 0.0615000
0.2000000 0.0695000
0.3000000 0.0775000
0.4000000 0.0785000
0.5000000 0.0740000
0.6000000 0.0670000
0.7000000 0.0555000
0.8000000 0.0410000
0.9000000 0.0230000
0.9500000 0.0120000
1.0000000 0.0000000
0.0000000 0.0045000
0.0125000 0.0000000
0.0250000 0.0005000
0.0500000 0.0035000
0.0750000 0.0065000
0.1000000 0.0105000
0.1500000 0.0175000
0.2000000 0.0235000
0.3000000 0.0320000
0.4000000 0.0355000
0.5000000 0.0330000
0.6000000 0.0290000
0.7000000 0.0215000
0.8000000 0.0145000
0.9000000 0.0070000
0.9500000 0.0035000
1.0000000 0.0000000
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Polars for GOE 427 AIRFOIL (goe427-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe427-il | 50,000 | 9 | 45.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 50,000 | 5 | 46.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 100,000 | 9 | 66.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 100,000 | 5 | 67.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 200,000 | 9 | 89 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 200,000 | 5 | 86.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 500,000 | 9 | 114.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 500,000 | 5 | 94.7 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 1,000,000 | 9 | 122.8 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 1,000,000 | 5 | 95 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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