GOE 652 AIRFOIL (goe652-il)
GOE 652 AIRFOIL - Gottingen 652 airfoil
| Details | Dat file | Parser | |
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(goe652-il) GOE 652 AIRFOIL Gottingen 652 airfoil Max thickness 17.1% at 20% chord. Max camber 9.3% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 652 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0377300
0.0250000 0.0534500
0.0500000 0.0754000
0.0750000 0.0913500
0.1000000 0.1043000
0.1500000 0.1227000
0.2000000 0.1361000
0.3000000 0.1479000
0.4000000 0.1497000
0.5000000 0.1415000
0.6000000 0.1253000
0.7000000 0.1016000
0.8000000 0.0719000
0.9000000 0.0387000
0.9500000 0.0206000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0302700
0.0250000 -.0415500
0.0500000 -.0501000
0.0750000 -.0526500
0.1000000 -.0522000
0.1500000 -.0458000
0.2000000 -.0344000
0.3000000 -.0061000
0.4000000 0.0222000
0.5000000 0.0435000
0.6000000 0.0563000
0.7000000 0.0596000
0.8000000 0.0514000
0.9000000 0.0312000
0.9500000 0.0166000
1.0000000 0.0000000
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Polars for GOE 652 AIRFOIL (goe652-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe652-il | 50,000 | 9 | 5.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 50,000 | 5 | 21.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 100,000 | 9 | 49.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 100,000 | 5 | 53.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 200,000 | 9 | 77.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 200,000 | 5 | 78 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 500,000 | 9 | 112.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 500,000 | 5 | 102.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 1,000,000 | 9 | 135.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 1,000,000 | 5 | 115.7 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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