GOE 531 AIRFOIL (goe531-il)
GOE 531 AIRFOIL - Gottingen 531 airfoil
| Details | Dat file | Parser | |
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(goe531-il) GOE 531 AIRFOIL Gottingen 531 airfoil Max thickness 13.8% at 19.5% chord. Max camber 14.7% at 49.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 531 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0114300 0.0328700
0.0233800 0.0497600
0.0476400 0.0725500
0.0720300 0.0913400
0.0965000 0.1076400
0.1456200 0.1347300
0.1948900 0.1573300
0.2938900 0.1880500
0.3932800 0.2067800
0.4932200 0.2085300
0.5937700 0.1918000
0.6949100 0.1565800
0.7963800 0.1113800
0.8981600 0.0566900
0.9490800 0.0283500
1.0000000 0.0000000
0.0000000 0.0000000
0.0133000 -.0245700
0.0259600 -.0296600
0.0509500 -.0293400
0.0757300 -.0225400
0.1004800 -.0147300
0.1499200 0.0023700
0.1993200 0.0209800
0.2982100 0.0551900
0.3975200 0.0764200
0.4972200 0.0856600
0.5974200 0.0794200
0.6980400 0.0601900
0.7988300 0.0359600
0.8995700 0.0132400
0.9497899 0.0063700
1.0000000 0.0000000
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Polars for GOE 531 AIRFOIL (goe531-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe531-il | 50,000 | 9 | 4.2 at α=16.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 50,000 | 5 | 7.1 at α=18.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 100,000 | 9 | 7.7 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 100,000 | 5 | 9.9 at α=18.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 200,000 | 9 | 13.7 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 200,000 | 5 | 13.5 at α=17.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 500,000 | 9 | 67.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 500,000 | 5 | 66.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 1,000,000 | 9 | 100.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 1,000,000 | 5 | 86.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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