GOE 596 AIRFOIL (goe596-il)
GOE 596 AIRFOIL - Gottingen 596 airfoil
| Details | Dat file | Parser | |
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(goe596-il) GOE 596 AIRFOIL Gottingen 596 airfoil Max thickness 9.8% at 30% chord. Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 596 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0212100
0.0250000 0.0294300
0.0500000 0.0418500
0.0750000 0.0522700
0.1000000 0.0607000
0.1500000 0.0725500
0.2000000 0.0809000
0.3000000 0.0881000
0.4000000 0.0873000
0.5000000 0.0795000
0.6000000 0.0682000
0.7000000 0.0549000
0.8000000 0.0381000
0.9000000 0.0198000
0.9500000 0.0101500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0127900
0.0250000 -.0150800
0.0500000 -.0156500
0.0750000 -.0157200
0.1000000 -.0153000
0.1500000 -.0144500
0.2000000 -.0126000
0.3000000 -.0094000
0.4000000 -.0067000
0.5000000 -.0045000
0.6000000 -.0033000
0.7000000 -.0026000
0.8000000 -.0019000
0.9000000 -.0007000
0.9500000 -.0003500
1.0000000 0.0000000
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Polars for GOE 596 AIRFOIL (goe596-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe596-il | 50,000 | 9 | 35.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 50,000 | 5 | 37 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 100,000 | 9 | 56.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 100,000 | 5 | 57.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 200,000 | 9 | 77.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 200,000 | 5 | 75.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 500,000 | 9 | 105.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 500,000 | 5 | 97.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 1,000,000 | 9 | 125.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 1,000,000 | 5 | 112.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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