GOE 311 (MVA H.43) AIRFOIL (goe311-il)
GOE 311 (MVA H.43) AIRFOIL - Gottingen 311 (MVA H.43) airfoil
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(goe311-il) GOE 311 (MVA H.43) AIRFOIL Gottingen 311 (MVA H.43) airfoil Max thickness 8.4% at 19.9% chord. Max camber 6.1% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 311 (MVA H.43) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123000 0.0192300
0.0246800 0.0299600
0.0495100 0.0461200
0.0744000 0.0569900
0.0992900 0.0673500
0.1491300 0.0816800
0.1990300 0.0912100
0.2989300 0.1012700
0.3989300 0.1007300
0.4990400 0.0906900
0.5991700 0.0784500
0.6993500 0.0615100
0.7995400 0.0434800
0.8997600 0.0223400
0.9498800 0.0111700
1.0000000 0.0021000
0.0000000 0.0000000
0.0125900 -.0083700
0.0251300 -.0119300
0.0501300 -.0121700
0.0751300 -.0119000
0.1001000 -.0092400
0.1500100 -.0005100
0.1999300 0.0069200
0.2998100 0.0180800
0.3997800 0.0207400
0.4998300 0.0165000
0.5998900 0.0100600
0.6999600 0.0037200
0.8000200 -.0015200
0.9000300 -.0028600
0.9500300 -.0026300
1.0000000 -.0021000
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Polars for GOE 311 (MVA H.43) AIRFOIL (goe311-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe311-il | 50,000 | 9 | 14.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe311-il | 50,000 | 5 | 34.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe311-il | 100,000 | 9 | 57.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe311-il | 100,000 | 5 | 59.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe311-il | 200,000 | 9 | 82.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe311-il | 200,000 | 5 | 82 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe311-il | 500,000 | 9 | 114 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe311-il | 500,000 | 5 | 106.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe311-il | 1,000,000 | 9 | 136.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe311-il | 1,000,000 | 5 | 97.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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