GOE 617 AIRFOIL (goe617-il)
GOE 617 AIRFOIL - Gottingen 617 airfoil
| Details | Dat file | Parser | |
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(goe617-il) GOE 617 AIRFOIL Gottingen 617 airfoil Max thickness 13.9% at 30% chord. Max camber 2.2% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 617 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0235000
0.0250000 0.0345000
0.0500000 0.0485000
0.0750000 0.0580000
0.1000000 0.0655000
0.1500000 0.0760000
0.2000000 0.0840000
0.3000000 0.0910000
0.4000000 0.0900000
0.5000000 0.0830000
0.6000000 0.0720000
0.7000000 0.0580000
0.8000000 0.0405000
0.9000000 0.0210000
0.9500000 0.0110000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0165000
0.0250000 -.0230000
0.0500000 -.0305000
0.0750000 -.0345000
0.1000000 -.0380000
0.1500000 -.0425000
0.2000000 -.0445000
0.3000000 -.0475000
0.4000000 -.0465000
0.5000000 -.0435000
0.6000000 -.0390000
0.7000000 -.0330000
0.8000000 -.0250000
0.9000000 -.0140000
0.9500000 -.0075000
1.0000000 0.0000000
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Polars for GOE 617 AIRFOIL (goe617-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe617-il | 50,000 | 9 | 29.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe617-il | 50,000 | 5 | 31.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe617-il | 100,000 | 9 | 49.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe617-il | 100,000 | 5 | 48.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe617-il | 200,000 | 9 | 67.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe617-il | 200,000 | 5 | 63 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe617-il | 500,000 | 9 | 87.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe617-il | 500,000 | 5 | 72.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe617-il | 1,000,000 | 9 | 91 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe617-il | 1,000,000 | 5 | 82.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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