GOE 310 (MVA H.42) AIRFOIL (goe310-il)
GOE 310 (MVA H.42) AIRFOIL - Gottingen 310 (MVA H.42) airfoil
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(goe310-il) GOE 310 (MVA H.42) AIRFOIL Gottingen 310 (MVA H.42) airfoil Max thickness 8.1% at 29.9% chord. Max camber 4.8% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 310 (MVA H.42) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123100 0.0176300
0.0247200 0.0259600
0.0496100 0.0366300
0.0744900 0.0483900
0.0994000 0.0570500
0.1492700 0.0686800
0.1991900 0.0766100
0.2990900 0.0856700
0.3990800 0.0867300
0.4991500 0.0803900
0.5992600 0.0697500
0.6994000 0.0566100
0.7995700 0.0406800
0.8997800 0.0211400
0.9498800 0.0110700
1.0000000 0.0000000
0.0000000 0.0000000
0.0126000 -.0094700
0.0251100 -.0108300
0.0501500 -.0137700
0.0751600 -.0151000
0.1001500 -.0145400
0.1501100 -.0106100
0.2000500 -.0042800
0.2999500 0.0042800
0.3999000 0.0095400
0.4999200 0.0074000
0.5999900 0.0010600
0.7000300 -.0031800
0.8000600 -.0058200
0.9000599 -.0052600
0.9500400 -.0037300
1.0000000 0.0000000
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Polars for GOE 310 (MVA H.42) AIRFOIL (goe310-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe310-il | 50,000 | 9 | 37.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe310-il | 50,000 | 5 | 38.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe310-il | 100,000 | 9 | 59.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe310-il | 100,000 | 5 | 58.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe310-il | 200,000 | 9 | 80.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe310-il | 200,000 | 5 | 73 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe310-il | 500,000 | 9 | 99.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe310-il | 500,000 | 5 | 72.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe310-il | 1,000,000 | 9 | 87.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe310-il | 1,000,000 | 5 | 87.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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