GOE 255 (MVA CA.6) AIRFOIL (goe255-il)
GOE 255 (MVA CA.6) AIRFOIL - Gottingen 255 (MVA CA.6) airfoil
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(goe255-il) GOE 255 (MVA CA.6) AIRFOIL Gottingen 255 (MVA CA.6) airfoil Max thickness 18.5% at 29.1% chord. Max camber 4.8% at 49.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 255 (MVA CA.6) AIRFOIL
17. 17.
0.0000100 0.0000000
0.0108500 0.0239500
0.0223200 0.0387500
0.0457500 0.0613700
0.0696700 0.0770300
0.0937900 0.0897000
0.1425200 0.1080800
0.1915900 0.1214800
0.2906900 0.1343400
0.3903900 0.1387500
0.4909900 0.1300200
0.5920900 0.1142300
0.6936901 0.0910700
0.7955101 0.0648300
0.8974800 0.0364000
0.9486901 0.0189400
1.0000000 0.0025000
0.0000100 0.0000000
0.0135200 -.0146600
0.0265400 -.0221600
0.0522400 -.0321800
0.0776900 -.0387200
0.1030300 -.0436600
0.1534300 -.0493700
0.2035900 -.0516900
0.3035200 -.0507700
0.4028700 -.0413800
0.5022200 -.0320000
0.6016200 -.0233100
0.7010900 -.0157100
0.8006800 -.0098100
0.9004100 -.0059000
0.9502700 -.0039500
1.0000000 -.0025000
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Polars for GOE 255 (MVA CA.6) AIRFOIL (goe255-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe255-il | 50,000 | 9 | 5.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 50,000 | 5 | 15.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 100,000 | 9 | 41.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 100,000 | 5 | 47.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 200,000 | 9 | 72.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 200,000 | 5 | 71.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 500,000 | 9 | 105.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 500,000 | 5 | 90.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 1,000,000 | 9 | 127.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 1,000,000 | 5 | 96.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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