GOE 496 AIRFOIL (goe496-il)
GOE 496 AIRFOIL - Gottingen 496 airfoil
| Details | Dat file | Parser | |
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(goe496-il) GOE 496 AIRFOIL Gottingen 496 airfoil Max thickness 10% at 30% chord. Max camber 5% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 496 AIRFOIL
15. 15.
0.0000000 0.0000000
0.0125000 0.0198100
0.0250000 0.0291200
0.0500000 0.0427500
0.0750000 0.0533800
0.1000000 0.0620000
0.2000000 0.0825000
0.3000000 0.0925000
0.4000000 0.0945000
0.5000000 0.0895000
0.6000000 0.0795000
0.7000000 0.0650000
0.8000000 0.0470000
0.9000000 0.0260000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0136900
0.0250000 -.0178800
0.0500000 -.0212500
0.0750000 -.0231300
0.1000000 -.0225000
0.2000000 -.0165000
0.3000000 -.0070000
0.4000000 0.0025000
0.5000000 0.0105000
0.6000000 0.0150000
0.7000000 0.0175000
0.8000000 0.0150000
0.9000000 0.0100000
1.0000000 0.0000000
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Polars for GOE 496 AIRFOIL (goe496-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe496-il | 50,000 | 9 | 37.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe496-il | 50,000 | 5 | 41 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe496-il | 100,000 | 9 | 62.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe496-il | 100,000 | 5 | 65 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe496-il | 200,000 | 9 | 89.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe496-il | 200,000 | 5 | 87.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe496-il | 500,000 | 9 | 124.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe496-il | 500,000 | 5 | 115.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe496-il | 1,000,000 | 9 | 150.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe496-il | 1,000,000 | 5 | 124 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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