GOE 477 AIRFOIL (goe477-il)
GOE 477 AIRFOIL - Gottingen 477 airfoil
| Details | Dat file | Parser | |
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(goe477-il) GOE 477 AIRFOIL Gottingen 477 airfoil Max thickness 10.1% at 30% chord. Max camber 4.9% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 477 AIRFOIL
13. 13.
0.0000000 0.0000000
0.0250000 0.0289100
0.0500000 0.0443200
0.1000000 0.0681500
0.2000000 0.0898000
0.3000000 0.0969500
0.4000000 0.0975000
0.5000000 0.0942500
0.6000000 0.0849000
0.7000000 0.0690500
0.8000000 0.0457000
0.9000000 0.0233500
1.0000000 0.0000000
0.0000000 0.0000000
0.0250000 -.0130900
0.0500000 -.0151800
0.1000000 -.0143500
0.2000000 -.0087000
0.3000000 -.0035500
0.4000000 0.0001000
0.5000000 0.0022500
0.6000000 0.0034000
0.7000000 0.0030500
0.8000000 0.0022000
0.9000000 0.0013500
1.0000000 0.0000000
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Polars for GOE 477 AIRFOIL (goe477-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe477-il | 50,000 | 9 | 34.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 50,000 | 5 | 36.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 100,000 | 9 | 56.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 100,000 | 5 | 54.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 200,000 | 9 | 80.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 200,000 | 5 | 75 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 500,000 | 9 | 111.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 500,000 | 5 | 87.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 1,000,000 | 9 | 121.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 1,000,000 | 5 | 104.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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