GOE 227 (MVA H.37) AIRFOIL (goe227-il)
GOE 227 (MVA H.37) AIRFOIL - Gottingen 227 (MVA H.37) airfoil
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(goe227-il) GOE 227 (MVA H.37) AIRFOIL Gottingen 227 (MVA H.37) airfoil Max thickness 14.6% at 25% chord. Max camber 7.8% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 227 (MVA H.37) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0253600
0.0250000 0.0377300
0.0500000 0.0584500
0.0750000 0.0751700
0.1000000 0.0879000
0.1500000 0.1083500
0.2000000 0.1228000
0.2500000 0.1322500
0.3000000 0.1377000
0.4000000 0.1406000
0.5000000 0.1355000
0.6000000 0.1184000
0.7000000 0.0973000
0.8000000 0.0692000
0.9000000 0.0381000
1.0000000 0.0030000
0.0000000 0.0000000
0.0125000 -.0166400
0.0250000 -.0222700
0.0500000 -.0265500
0.0750000 -.0268200
0.1000000 -.0261000
0.1500000 -.0226500
0.2000000 -.0192000
0.2500000 -.0137500
0.3000000 -.0063000
0.4000000 0.0086000
0.5000000 0.0215000
0.6000000 0.0314000
0.7000000 0.0343000
0.8000000 0.0322000
0.9000000 0.0201000
1.0000000 0.0000000
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Polars for GOE 227 (MVA H.37) AIRFOIL (goe227-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe227-il | 50,000 | 9 | 7.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe227-il | 50,000 | 5 | 23.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe227-il | 100,000 | 9 | 49.6 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe227-il | 100,000 | 5 | 58.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe227-il | 200,000 | 9 | 88 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe227-il | 200,000 | 5 | 88.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe227-il | 500,000 | 9 | 131.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe227-il | 500,000 | 5 | 118.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe227-il | 1,000,000 | 9 | 155.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe227-il | 1,000,000 | 5 | 134.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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