GOE 797 AIRFOIL (goe797-il)
GOE 797 AIRFOIL - Gottingen 797 airfoil
| Details | Dat file | Parser | |
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(goe797-il) GOE 797 AIRFOIL Gottingen 797 airfoil Max thickness 16% 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 797 AIRFOIL
14. 14.
0.0000000 0.0000000
0.0125000 0.0276000
0.0250000 0.0412000
0.0500000 0.0604000
0.1500000 0.1022000
0.2000000 0.1146000
0.3000000 0.1264000
0.4000000 0.1292000
0.5000000 0.1240000
0.6000000 0.1104000
0.7000000 0.0906000
0.8000000 0.0674000
0.9000000 0.0392000
1.0000000 0.0080000
0.0000000 0.0000000
0.0125000 -.0214000
0.0250000 -.0288000
0.0500000 -.0360000
0.1500000 -.0400000
0.2000000 -.0384000
0.3000000 -.0336000
0.4000000 -.0288000
0.5000000 -.0240000
0.6000000 -.0192000
0.7000000 -.0144000
0.8000000 -.0096000
0.9000000 -.0048000
1.0000000 0.0000000
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Polars for GOE 797 AIRFOIL (goe797-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe797-il | 50,000 | 9 | 7.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe797-il | 50,000 | 5 | 20.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe797-il | 100,000 | 9 | 48.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe797-il | 100,000 | 5 | 50.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe797-il | 200,000 | 9 | 76 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe797-il | 200,000 | 5 | 73.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe797-il | 500,000 | 9 | 108.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe797-il | 500,000 | 5 | 96.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe797-il | 1,000,000 | 9 | 128.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe797-il | 1,000,000 | 5 | 106.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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