GOE 627 AIRFOIL (goe627-il)
GOE 627 AIRFOIL - Gottingen 627 airfoil
| Details | Dat file | Parser | |
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(goe627-il) GOE 627 AIRFOIL Gottingen 627 airfoil Max thickness 15.8% at 30% chord. Max camber 4.1% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 627 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0350000
0.0250000 0.0500000
0.0500000 0.0705000
0.0750000 0.0840000
0.1000000 0.0945000
0.1500000 0.1085000
0.2000000 0.1155000
0.3000000 0.1195000
0.4000000 0.1160000
0.5000000 0.1075000
0.6000000 0.0945000
0.7000000 0.0780000
0.8000000 0.0575000
0.9000000 0.0315000
0.9500000 0.0160000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0125000
0.0250000 -.0170000
0.0500000 -.0230000
0.0750000 -.0270000
0.1000000 -.0305000
0.1500000 -.0345000
0.2000000 -.0370000
0.3000000 -.0380000
0.4000000 -.0370000
0.5000000 -.0345000
0.6000000 -.0305000
0.7000000 -.0250000
0.8000000 -.0180000
0.9000000 -.0095000
0.9500000 -.0050000
1.0000000 0.0000000
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Polars for GOE 627 AIRFOIL (goe627-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe627-il | 50,000 | 9 | 25.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe627-il | 50,000 | 5 | 29.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe627-il | 100,000 | 9 | 43.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe627-il | 100,000 | 5 | 41.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe627-il | 200,000 | 9 | 55.2 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe627-il | 200,000 | 5 | 52.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe627-il | 500,000 | 9 | 74.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe627-il | 500,000 | 5 | 71.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe627-il | 1,000,000 | 9 | 93.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe627-il | 1,000,000 | 5 | 90.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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