GOE 612 AIRFOIL (goe612-il)
GOE 612 AIRFOIL - Gottingen 612 airfoil
| Details | Dat file | Parser | |
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(goe612-il) GOE 612 AIRFOIL Gottingen 612 airfoil Max thickness 15% at 29.5% chord. Max camber 5% at 49.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 612 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0112900 0.0265100
0.0231600 0.0405500
0.0472200 0.0611500
0.0715500 0.0757600
0.0960700 0.0863700
0.1453800 0.1016100
0.1949300 0.1113700
0.2945500 0.1199000
0.3945000 0.1209500
0.4947900 0.1145100
0.5954500 0.1000900
0.6963500 0.0801800
0.7974200 0.0567800
0.8987100 0.0283900
0.9494000 0.0132000
1.0000000 0.0000000
0.0000000 0.0000000
0.0134300 -.0203900
0.0262000 -.0263100
0.0514600 -.0321600
0.0766200 -.0355100
0.1016800 -.0368700
0.1517100 -.0376000
0.2016500 -.0363200
0.3013600 -.0297900
0.4009700 -.0212600
0.5006200 -.0137200
0.6004000 -.0086800
0.7002600 -.0056400
0.8001400 -.0030900
0.9000700 -.0015500
0.9500600 -.0012700
1.0000000 0.0000000
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Polars for GOE 612 AIRFOIL (goe612-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe612-il | 50,000 | 9 | 9.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 50,000 | 5 | 27.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe612-il | 100,000 | 9 | 51.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 100,000 | 5 | 49.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe612-il | 200,000 | 9 | 74.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 200,000 | 5 | 70.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe612-il | 500,000 | 9 | 105.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 500,000 | 5 | 85.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe612-il | 1,000,000 | 9 | 121.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 1,000,000 | 5 | 100 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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