GOE 801 (MVA 301) AIRFOIL (goe801-il)
GOE 801 (MVA 301) AIRFOIL - Gottingen 801 (MVA 301) airfoil
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(goe801-il) GOE 801 (MVA 301) AIRFOIL Gottingen 801 (MVA 301) 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 801 (MVA 301) 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 801 (MVA 301) AIRFOIL (goe801-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe801-il | 50,000 | 9 | 17.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe801-il | 50,000 | 5 | 38.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe801-il | 100,000 | 9 | 55.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe801-il | 100,000 | 5 | 60.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe801-il | 200,000 | 9 | 79.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe801-il | 200,000 | 5 | 79.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe801-il | 500,000 | 9 | 110.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe801-il | 500,000 | 5 | 104.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe801-il | 1,000,000 | 9 | 132 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe801-il | 1,000,000 | 5 | 123 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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