GOE 426 AIRFOIL (goe426-il)
GOE 426 AIRFOIL - Gottingen 426 airfoil
| Details | Dat file | Parser | |
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(goe426-il) GOE 426 AIRFOIL Gottingen 426 airfoil Max thickness 13.6% at 30% chord. Max camber 4.6% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 426 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0214400
0.0250000 0.0323700
0.0500000 0.0487500
0.0750000 0.0616200
0.1000000 0.0720000
0.1500000 0.0887500
0.2000000 0.1005000
0.3000000 0.1115000
0.4000000 0.1105000
0.5000000 0.1000000
0.6000000 0.0850000
0.7000000 0.0660000
0.8000000 0.0455000
0.9000000 0.0225000
0.9500000 0.0107500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0170600
0.0250000 -.0206300
0.0500000 -.0229800
0.0750000 -.0248700
0.1000000 -.0255000
0.1500000 -.0262500
0.2000000 -.0265000
0.3000000 -.0245000
0.4000000 -.0195000
0.5000000 -.0140000
0.6000000 -.0075000
0.7000000 -.0020000
0.8000000 0.0020000
0.9000000 0.0025000
0.9500000 0.0017500
1.0000000 0.0000000
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Polars for GOE 426 AIRFOIL (goe426-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe426-il | 50,000 | 9 | 7.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe426-il | 50,000 | 5 | 26.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe426-il | 100,000 | 9 | 46.9 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe426-il | 100,000 | 5 | 52.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe426-il | 200,000 | 9 | 75.9 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe426-il | 200,000 | 5 | 77.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe426-il | 500,000 | 9 | 112.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe426-il | 500,000 | 5 | 110.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe426-il | 1,000,000 | 9 | 141.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe426-il | 1,000,000 | 5 | 134.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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