GOE 124 (MVA H.4) AIRFOIL (goe124-il)
GOE 124 (MVA H.4) AIRFOIL - Gottingen 124 (MVA H.4) airfoil
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(goe124-il) GOE 124 (MVA H.4) AIRFOIL Gottingen 124 (MVA H.4) airfoil Max thickness 7.9% at 29.9% chord. Max camber 5.6% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 124 (MVA H.4) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123200 0.0210500
0.0247400 0.0310100
0.0496200 0.0450200
0.0745300 0.0551300
0.0994600 0.0629500
0.1493500 0.0759700
0.1992700 0.0855900
0.2992100 0.0932400
0.3992100 0.0929900
0.4992700 0.0861400
0.5993700 0.0737900
0.6995100 0.0581500
0.7996600 0.0404000
0.8998200 0.0213500
0.9499000 0.0118700
1.0000000 0.0025000
0.0000000 0.0000000
0.0125900 -.0108900
0.0250900 -.0107900
0.0500600 -.0072700
0.0750400 -.0046600
0.1000200 -.0021500
0.1499800 0.0023700
0.1999400 0.0072000
0.2998800 0.0140500
0.3998500 0.0182000
0.4998300 0.0196500
0.5998500 0.0172000
0.6998800 0.0141500
0.7999099 0.0101000
0.8999600 0.0048500
0.9499800 0.0019700
1.0000000 -.0025000
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Polars for GOE 124 (MVA H.4) AIRFOIL (goe124-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe124-il | 50,000 | 9 | 35.9 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe124-il | 50,000 | 5 | 41.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe124-il | 100,000 | 9 | 60.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe124-il | 100,000 | 5 | 63.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe124-il | 200,000 | 9 | 84.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe124-il | 200,000 | 5 | 83.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe124-il | 500,000 | 9 | 114.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe124-il | 500,000 | 5 | 107.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe124-il | 1,000,000 | 9 | 133.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe124-il | 1,000,000 | 5 | 126.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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