Similarly shaped airfoils to GA 35A610
New! Bulk download of polars in Excel format: GA%2035A610.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 40A610
3. GA 40-610
4. GA 37-610
5. GA 30-610
6. GA 35-610
7. GA 30A610
8. NACA64-610 a=0.5
9. NACA65-610 a=0.5
10. NACA64-610 a=0.6
11. NACA65-610 a=0.6
12. NACA63-610 a=0.5
13. GA 37-611
14. NACA63-610 a=0.6
15. GA 35-611
16. NACA64-710 a=0.5
17. PSU 94-097 (AIAA 2001-2478)
18. GA 35A611
19. GA 37A611
20. NACA63-710 a=0.5
21. GA 40A611