Similarly shaped airfoils to NACA65-511 a=0.6
New! Bulk download of polars in Excel format: NACA65-511%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. GA 40-411
3. GA 40A411
4. NACA64-511 a=0.6
5. GA 37A411
6. NACA64-511 a=0.5
7. NACA65-511 a=0.8
8. GA 35A411
9. S4158
10. NACA63-511 a=0.6
11. GA 37-411
12. NACA65-512 a=0.6
13. NACA65-510 a=0.6
14. NACA64A511
15. NACA66-511 a=0.6
16. NACA63-511 a=0.5
17. NACA64-512 a=0.6
18. NACA65-611
19. NACA64-511 a=0.8
20. NACA65-510 a=0.5
21. NACA63A511