Similarly shaped airfoils to GA 35A411
New! Bulk download of polars in Excel format: GA%2035A411.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 40A411
3. GA 40-411
4. GA 37-411
5. NACA64-511 a=0.5
6. K3311 (smoothed)
7. NACA64-511 a=0.6
8. GA 30-411
9. NACA65-511 a=0.5
10. NACA63-511 a=0.5
11. GA 35-411
12. K3311 (original)
13. GA 30A411
14. NACA63-511 a=0.6
15. NACA65-511 a=0.6
16. GA 37-412
17. MS3/11GPV
18. HQ 3.0/11
19. NACA64-512 a=0.5
20. GA 30-410
21. GA 35A410