GOE 449 AIRFOIL (goe449-il)
GOE 449 AIRFOIL - Gottingen 449 airfoil
| Details | Dat file | Parser | |
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(goe449-il) GOE 449 AIRFOIL Gottingen 449 airfoil Max thickness 17% at 30% chord. Max camber 5.4% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 449 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0312000
0.0250000 0.0454000
0.0500000 0.0653000
0.0750000 0.0802000
0.1000000 0.0916000
0.1500000 0.1094000
0.2000000 0.1217000
0.3000000 0.1358000
0.4000000 0.1384000
0.5000000 0.1310000
0.6000000 0.1171000
0.7000000 0.0952000
0.8000000 0.0673000
0.9000000 0.0354000
0.9500000 0.0182000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0178000
0.0250000 -.0241000
0.0500000 -.0307000
0.0750000 -.0338000
0.1000000 -.0354000
0.1500000 -.0366000
0.2000000 -.0363000
0.3000000 -.0337000
0.4000000 -.0306000
0.5000000 -.0260000
0.6000000 -.0224000
0.7000000 -.0168000
0.8000000 -.0112000
0.9000000 -.0046000
0.9500000 -.0013000
1.0000000 0.0000000
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Polars for GOE 449 AIRFOIL (goe449-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe449-il | 50,000 | 9 | 4.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe449-il | 50,000 | 5 | 12.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe449-il | 100,000 | 9 | 34.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe449-il | 100,000 | 5 | 43.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe449-il | 200,000 | 9 | 70.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe449-il | 200,000 | 5 | 65.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe449-il | 500,000 | 9 | 97.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe449-il | 500,000 | 5 | 87.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe449-il | 1,000,000 | 9 | 117.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe449-il | 1,000,000 | 5 | 107.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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