GOE 802 AIRFOIL (goe802-il)
GOE 802 AIRFOIL - Gottingen 802 airfoil
| Details | Dat file | Parser | |
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(goe802-il) GOE 802 AIRFOIL Gottingen 802 airfoil Max thickness 9.8% at 30% chord. Max camber 6.1% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 802 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0261500
0.0250000 0.0398000
0.0500000 0.0566000
0.0750000 0.0689000
0.1000000 0.0782000
0.1500000 0.0918000
0.2000000 0.1014000
0.3000000 0.1096000
0.4000000 0.1088000
0.5000000 0.1015000
0.6000000 0.0897000
0.7000000 0.0734000
0.8000000 0.0526000
0.9000000 0.0288000
0.9500000 0.0164000
1.0000000 0.0040000
0.0000000 0.0000000
0.0125000 -.0118500
0.0250000 -.0117000
0.0500000 -.0094000
0.0750000 -.0071000
0.1000000 -.0048000
0.1500000 -.0002000
0.2000000 0.0044000
0.3000000 0.0116000
0.4000000 0.0148000
0.5000000 0.0150000
0.6000000 0.0147000
0.7000000 0.0124000
0.8000000 0.0086000
0.9000000 0.0038000
0.9500000 0.0019000
1.0000000 0.0000000
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Polars for GOE 802 AIRFOIL (goe802-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe802-il | 50,000 | 9 | 17.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802-il | 50,000 | 5 | 38.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802-il | 100,000 | 9 | 55.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802-il | 100,000 | 5 | 60.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802-il | 200,000 | 9 | 79.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802-il | 200,000 | 5 | 79.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802-il | 500,000 | 9 | 110.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802-il | 500,000 | 5 | 104.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802-il | 1,000,000 | 9 | 132 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802-il | 1,000,000 | 5 | 123 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||