Similarly shaped airfoils to NACA65-713 a=0.6
New! Bulk download of polars in Excel format: NACA65-713%20a%3D0.6.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. NACA64-713 a=0.6
3. GA 40-613
4. GA 40A613
5. NACA65-714 a=0.6
6. NACA65-712 a=0.6
7. NACA64-713 a=0.5
8. GA 37A613
9. NACA64-714 a=0.6
10. NACA63-713 a=0.6
11. NACA65-712 a=0.5
12. GA 35A613
13. NACA65-713 a=0.8
14. NACA65-714 a=0.5
15. NACA66-713 a=0.6
16. NACA66-712 a=0.6
17. GA 37-613
18. NACA63-713 a=0.5
19. NACA64-714 a=0.5
20. GA 40-614
21. GA 40A614