GOE 398 AIRFOIL (goe398-il)
GOE 398 AIRFOIL - Gottingen 398 airfoil
| Details | Dat file | Parser | |
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(goe398-il) GOE 398 AIRFOIL Gottingen 398 airfoil Max thickness 13.9% at 30% chord. Max camber 4.9% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 398 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0343500
0.0250000 0.0457000
0.0500000 0.0619000
0.0750000 0.0751000
0.1000000 0.0858000
0.1500000 0.1002000
0.2000000 0.1091000
0.3000000 0.1169000
0.4000000 0.1147000
0.5000000 0.1070000
0.6000000 0.0928000
0.7000000 0.0741000
0.8000000 0.0519000
0.9000000 0.0277000
0.9500000 0.0146000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0121500
0.0250000 -.0168000
0.0500000 -.0216000
0.0750000 -.0239000
0.1000000 -.0252000
0.1500000 -.0258000
0.2000000 -.0244000
0.3000000 -.0216000
0.4000000 -.0176700
0.5000000 -.0135000
0.6000000 -.0097000
0.7000000 -.0069000
0.8000000 -.0051000
0.9000000 -.0033000
0.9500000 -.0029000
1.0000000 0.0000000
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Polars for GOE 398 AIRFOIL (goe398-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe398-il | 50,000 | 9 | 10.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe398-il | 50,000 | 5 | 31 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe398-il | 100,000 | 9 | 50.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe398-il | 100,000 | 5 | 51.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe398-il | 200,000 | 9 | 71.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe398-il | 200,000 | 5 | 68.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe398-il | 500,000 | 9 | 96.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe398-il | 500,000 | 5 | 92.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe398-il | 1,000,000 | 9 | 120.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe398-il | 1,000,000 | 5 | 112.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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