Similarly shaped airfoils to GA 37A411


New! Bulk download of polars in Excel format: GA%2037A411.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
Dynamic plotter New!
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

Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.

1. GA 35A411
2. GA 40A411
3. GA 40-411
4. NACA65-511 a=0.5
5. GA 37-411
6. NACA64-511 a=0.5
7. NACA65-511 a=0.6
8. NACA64-511 a=0.6
9. NACA63-511 a=0.5
10. GA 35-411
11. K3311 (smoothed)
12. GA 30-411
13. K3311 (original)
14. NACA63-511 a=0.6
15. GA 37-412
16. GA 30A411
17. GA 40A412
18. GA 37A412
19. GA 37A410
20. GA 40-412
21. GA 35A410