GOE 802 A AIRFOIL (goe802a-il)
GOE 802 A AIRFOIL - Gottingen 802 A airfoil
| Details | Dat file | Parser | |
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(goe802a-il) GOE 802 A AIRFOIL Gottingen 802 A 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 A AIRFOIL
17. 25.
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 -.0120000
0.0500000 -.0094000
0.0750000 -.0027000
0.0850000 0.0030000
0.0900000 0.0115000
0.0950000 0.0165000
0.1000000 0.0180000
0.1050000 0.0165000
0.1100000 0.0110000
0.1150000 0.0050000
0.1200000 0.0020000
0.1250000 0.0010000
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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Similar airfoils
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Polars for GOE 802 A AIRFOIL (goe802a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe802a-il | 50,000 | 9 | 27.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802a-il | 50,000 | 5 | 39.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802a-il | 100,000 | 9 | 52.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802a-il | 100,000 | 5 | 61 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802a-il | 200,000 | 9 | 73.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802a-il | 200,000 | 5 | 149.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802a-il | 500,000 | 9 | 101.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802a-il | 500,000 | 5 | 91 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802a-il | 1,000,000 | 9 | 101.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802a-il | 1,000,000 | 5 | 175 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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