Similarly shaped airfoils to GOE 559
New! Bulk download of polars in Excel format: goe559.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
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2. GA 37A411
3. GA 40-411
4. GA 35A411
5. NACA65-511 a=0.5
6. GA 37A410
7. GA 37-411
8. NACA64-511 a=0.5
9. GA 40A410
10. GA 35A410
11. NACA65-611 a=0.0
12. GA 40-410
13. NACA65-511 a=0.2
14. NACA64-611 a=0.0
15. NACA65-510 a=0.5
16. NACA65-510 a=0.2
17. NACA64-511 a=0.2
18. NACA65-610 a=0.0
19. NACA65-611 a=0.2
20. GA 35-411
21. NACA63-511 a=0.5