GOE 223 (MVA H.34) AIRFOIL (goe223-il)
GOE 223 (MVA H.34) AIRFOIL - Gottingen 223 (MVA H.34) airfoil
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(goe223-il) GOE 223 (MVA H.34) AIRFOIL Gottingen 223 (MVA H.34) airfoil Max thickness 18.8% at 29.1% chord. Max camber 5.7% at 49.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 223 (MVA H.34) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0109000 0.0247100
0.0224500 0.0392600
0.0459600 0.0622900
0.0698000 0.0800400
0.0940500 0.0916100
0.1426700 0.1127700
0.1917000 0.1255100
0.2908000 0.1416000
0.3906500 0.1438900
0.4913300 0.1339400
0.5922900 0.1187000
0.6937600 0.0960900
0.7956401 0.0671200
0.8977400 0.0348500
0.9488800 0.0171800
1.0000000 0.0010000
0.0000000 0.0000000
0.0134900 -.0151200
0.0262900 -.0197900
0.0518000 -.0276300
0.0771800 -.0334800
0.1024300 -.0373400
0.1528900 -.0443600
0.2031400 -.0483000
0.3030100 -.0463000
0.4022000 -.0338600
0.5012000 -.0184200
0.6002800 -.0042800
0.6995500 0.0069700
0.7992900 0.0109500
0.8994800 0.0079700
0.9497600 0.0037300
1.0000000 -.0010000
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Polars for GOE 223 (MVA H.34) AIRFOIL (goe223-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe223-il | 50,000 | 9 | 5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe223-il | 50,000 | 5 | 15.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe223-il | 100,000 | 9 | 43.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe223-il | 100,000 | 5 | 48.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe223-il | 200,000 | 9 | 73 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe223-il | 200,000 | 5 | 67 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe223-il | 500,000 | 9 | 95.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe223-il | 500,000 | 5 | 80.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe223-il | 1,000,000 | 9 | 108.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe223-il | 1,000,000 | 5 | 80.4 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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