GOE 411 AIRFOIL (goe411-il)
GOE 411 AIRFOIL - Gottingen 411 airfoil
| Details | Dat file | Parser | |
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(goe411-il) GOE 411 AIRFOIL Gottingen 411 airfoil Max thickness 13.2% at 30% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 411 AIRFOIL
16. 16.
0.0000000 0.0000000
0.0125000 0.0115000
0.0250000 0.0184000
0.0500000 0.0305000
0.0750000 0.0388000
0.1000000 0.0460000
0.1500000 0.0550000
0.2000000 0.0605000
0.3000000 0.0660000
0.4000000 0.0655000
0.5000000 0.0605000
0.6000000 0.0530000
0.7000000 0.0440000
0.8000000 0.0320000
0.9000000 0.0180000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0115000
0.0250000 -.0184000
0.0500000 -.0305000
0.0750000 -.0388000
0.1000000 -.0460000
0.1500000 -.0550000
0.2000000 -.0605000
0.3000000 -.0660000
0.4000000 -.0655000
0.5000000 -.0605000
0.6000000 -.0530000
0.7000000 -.0440000
0.8000000 -.0320000
0.9000000 -.0180000
1.0000000 0.0000000
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Polars for GOE 411 AIRFOIL (goe411-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe411-il | 50,000 | 9 | 30.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe411-il | 50,000 | 5 | 28 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe411-il | 100,000 | 9 | 40.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe411-il | 100,000 | 5 | 34.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe411-il | 200,000 | 9 | 43.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe411-il | 200,000 | 5 | 35.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe411-il | 500,000 | 9 | 45.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe411-il | 500,000 | 5 | 42.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe411-il | 1,000,000 | 9 | 48.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe411-il | 1,000,000 | 5 | 53.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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