GOE 328 AIRFOIL (goe328-il)
GOE 328 AIRFOIL - Gottingen 328 airfoil
| Details | Dat file | Parser | |
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(goe328-il) GOE 328 AIRFOIL Gottingen 328 airfoil Max thickness 8.2% at 30% chord. Max camber 4.3% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 328 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0171900
0.0250000 0.0253700
0.0500000 0.0377500
0.0750000 0.0481300
0.1000000 0.0565000
0.1500000 0.0702500
0.2000000 0.0780000
0.3000000 0.0845000
0.4000000 0.0830000
0.5000000 0.0775000
0.6000000 0.0670000
0.7000000 0.0535000
0.8000000 0.0380000
0.9000000 0.0215000
0.9500000 0.0132500
1.0000000 0.0050000
0.0000000 0.0000000
0.0125000 -.0138100
0.0250000 -.0146200
0.0500000 -.0122500
0.0750000 -.0098800
0.1000000 -.0075000
0.1500000 -.0037500
0.2000000 -.0010000
0.3000000 0.0025000
0.4000000 0.0040000
0.5000000 0.0045000
0.6000000 0.0040000
0.7000000 0.0030000
0.8000000 0.0020000
0.9000000 0.0010000
0.9500000 0.0007500
1.0000000 0.0000000
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Polars for GOE 328 AIRFOIL (goe328-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe328-il | 50,000 | 9 | 36.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe328-il | 50,000 | 5 | 39.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe328-il | 100,000 | 9 | 56.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe328-il | 100,000 | 5 | 57.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe328-il | 200,000 | 9 | 75.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe328-il | 200,000 | 5 | 74.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe328-il | 500,000 | 9 | 101.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe328-il | 500,000 | 5 | 96.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe328-il | 1,000,000 | 9 | 120.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe328-il | 1,000,000 | 5 | 111.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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