Similarly shaped airfoils to GA 40A616
New! Bulk download of polars in Excel format: GA%2040A616.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
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.
2. GA 37A616
3. NACA65-716 a=0.5
4. GA 35A616
5. NACA65-716 a=0.6
6. GA 37-616
7. GA 40A615
8. GA 40-617
9. GA 40A617
10. GA 37A615
11. GA 40-615
12. EPPLER 431
13. NACA65-616 a=0.6
14. GA 35A615
15. EPPLER 657
16. NACA65-715 a=0.5
17. NACA64-716 a=0.5
18. EPPLER 432
19. NACA65-616 a=0.5
20. NACA65-717 a=0.5
21. GA 37-617