GOE 122 (MVA H.2) AIRFOIL (goe122-il)
GOE 122 (MVA H.2) AIRFOIL - Gottingen 122 (MVA H.2) airfoil
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(goe122-il) GOE 122 (MVA H.2) AIRFOIL Gottingen 122 (MVA H.2) airfoil Max thickness 7.3% at 30% chord. Max camber 4.1% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 122 (MVA H.2) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123800 0.0183800
0.0248300 0.0256600
0.0497600 0.0379200
0.0746900 0.0480800
0.0996400 0.0559400
0.1495800 0.0656600
0.1995300 0.0725900
0.2995000 0.0771300
0.3995300 0.0738800
0.4995700 0.0673200
0.5996300 0.0569700
0.6997100 0.0449100
0.7998000 0.0306600
0.8999000 0.0152000
0.9499500 0.0083300
1.0000000 0.0012500
0.0000000 0.0000000
0.0125500 -.0076200
0.0250500 -.0075400
0.0500400 -.0067800
0.0750400 -.0055200
0.1000300 -.0042500
0.1500200 -.0023300
0.2000000 -.0003100
0.2999700 0.0041300
0.3999600 0.0059800
0.4999600 0.0066200
0.5999600 0.0055700
0.6999800 0.0034100
0.7999800 0.0015700
0.9000000 -.0001900
0.9500100 -.0009700
1.0000000 -.0012500
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Polars for GOE 122 (MVA H.2) AIRFOIL (goe122-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe122-il | 50,000 | 9 | 37.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 50,000 | 5 | 39.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 100,000 | 9 | 55.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 100,000 | 5 | 56.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 200,000 | 9 | 73.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 200,000 | 5 | 72.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 500,000 | 9 | 95.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 500,000 | 5 | 89.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 1,000,000 | 9 | 110.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 1,000,000 | 5 | 97.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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