GOE 621 AIRFOIL (goe621-il)
GOE 621 AIRFOIL - Gottingen 621 airfoil
| Details | Dat file | Parser | |
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(goe621-il) GOE 621 AIRFOIL Gottingen 621 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 621 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
0.9001200 -.0025400
0.9500600 -.0012700
1.0000000 0.0000000
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Polars for GOE 621 AIRFOIL (goe621-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe621-il | 50,000 | 9 | 9.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe621-il | 50,000 | 5 | 27.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe621-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe621-il | 100,000 | 5 | 49.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe621-il | 200,000 | 9 | 74.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe621-il | 200,000 | 5 | 70.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe621-il | 500,000 | 9 | 105.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe621-il | 500,000 | 5 | 84.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe621-il | 1,000,000 | 9 | 120.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe621-il | 1,000,000 | 5 | 99.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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