GOE 517 AIRFOIL (goe517-il)
GOE 517 AIRFOIL - Gottingen 517 airfoil
| Details | Dat file | Parser | |
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(goe517-il) GOE 517 AIRFOIL Gottingen 517 airfoil Max thickness 7% at 30% chord. Max camber 4.7% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 517 AIRFOIL
13. 13.
0.0000000 0.0000000
0.0250000 0.0246900
0.0500000 0.0373700
0.1000000 0.0552500
0.2000000 0.0745000
0.3000000 0.0807500
0.4000000 0.0810000
0.5000000 0.0747500
0.6000000 0.0660000
0.7000000 0.0532500
0.8000000 0.0370000
0.9000000 0.0197500
1.0000000 0.0000000
0.0000000 0.0000000
0.0250000 -.0068100
0.0500000 -.0071200
0.1000000 -.0027500
0.2000000 0.0060000
0.3000000 0.0107500
0.4000000 0.0120000
0.5000000 0.0112500
0.6000000 0.0090000
0.7000000 0.0052500
0.8000000 0.0030000
0.9000000 0.0007500
1.0000000 0.0000000
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Similar airfoils
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Polars for GOE 517 AIRFOIL (goe517-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe517-il | 50,000 | 9 | 37.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 50,000 | 5 | 40.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 100,000 | 9 | 55.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 100,000 | 5 | 60.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 200,000 | 9 | 75 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 200,000 | 5 | 79.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 500,000 | 9 | 103 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 500,000 | 5 | 102 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 1,000,000 | 9 | 121.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 1,000,000 | 5 | 117.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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