GOE 222 (MVA H.33) AIRFOIL (goe222-il)
GOE 222 (MVA H.33) AIRFOIL - Gottingen 222 (MVA H.33) airfoil
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(goe222-il) GOE 222 (MVA H.33) AIRFOIL Gottingen 222 (MVA H.33) airfoil Max thickness 18.5% at 29.2% chord. Max camber 7.2% at 49.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 222 (MVA H.33) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0109700 0.0285900
0.0226900 0.0432100
0.0465300 0.0649900
0.0705200 0.0837700
0.0947600 0.0980700
0.1436300 0.1191800
0.1928800 0.1331200
0.2919400 0.1506200
0.3917900 0.1534600
0.4920900 0.1478300
0.5928200 0.1342200
0.6941100 0.1101300
0.7956401 0.0815700
0.8975900 0.0450200
0.9487400 0.0235600
1.0000000 0.0015000
0.0000000 0.0000000
0.0134000 -.0167800
0.0262100 -.0226000
0.0515900 -.0297400
0.0769100 -.0355900
0.1020900 -.0390400
0.1522900 -.0428500
0.2023100 -.0431800
0.3018100 -.0338500
0.4009700 -.0180500
0.5001700 -.0032400
0.5995200 0.0090700
0.6992000 0.0149100
0.7991900 0.0150600
0.8994300 0.0106200
0.9496900 0.0058100
1.0000000 -.0015000
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Polars for GOE 222 (MVA H.33) AIRFOIL (goe222-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe222-il | 50,000 | 9 | 5.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 50,000 | 5 | 14.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 100,000 | 9 | 42.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 100,000 | 5 | 47.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 200,000 | 9 | 74.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 200,000 | 5 | 67.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 500,000 | 9 | 99.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 500,000 | 5 | 84.8 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 1,000,000 | 9 | 115.2 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 1,000,000 | 5 | 102 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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