GOE 134 (MVA H.12) AIRFOIL (goe134-il)
GOE 134 (MVA H.12) AIRFOIL - Gottingen 134 (MVA H.12) airfoil
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(goe134-il) GOE 134 (MVA H.12) AIRFOIL Gottingen 134 (MVA H.12) airfoil Max thickness 9.5% at 30% chord. Max camber 4% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 134 (MVA H.12) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0207100
0.0250000 0.0311200
0.0500000 0.0450400
0.0750000 0.0552700
0.1000000 0.0632900
0.1500000 0.0754300
0.2000000 0.0826800
0.3000000 0.0882700
0.4000000 0.0868600
0.5000000 0.0805500
0.6000000 0.0707400
0.7000000 0.0583300
0.8000000 0.0452200
0.9000000 0.0286100
0.9500000 0.0190600
1.0000000 0.0090000
0.0000000 0.0000000
0.0125000 -.0087900
0.0250000 -.0086800
0.0500000 -.0084500
0.0750000 -.0082300
0.1000000 -.0080100
0.1500000 -.0075700
0.2000000 -.0071200
0.3000000 -.0062300
0.4000000 -.0053400
0.5000000 -.0044500
0.6000000 -.0035600
0.7000000 -.0026700
0.8000000 -.0017800
0.9000000 -.0008900
0.9500000 -.0004500
1.0000000 0.0000000
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Polars for GOE 134 (MVA H.12) AIRFOIL (goe134-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe134-il | 50,000 | 9 | 29.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 50,000 | 5 | 38.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 100,000 | 9 | 50.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 100,000 | 5 | 55.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 200,000 | 9 | 70.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 200,000 | 5 | 71.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 500,000 | 9 | 96.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 500,000 | 5 | 93.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 1,000,000 | 9 | 114.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 1,000,000 | 5 | 109.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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