Similarly shaped airfoils to NACA65-511 a=0.5
New! Bulk download of polars in Excel format: NACA65-511%20a%3D0.5.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. GA 37A411
5. NACA64-511 a=0.5
6. GA 35A411
7. NACA64-511 a=0.6
8. GA 37-411
9. NACA63-511 a=0.5
10. NACA65-512 a=0.5
11. S4158
12. NACA65-510 a=0.5
13. NACA66-511 a=0.5
14. NACA63-511 a=0.6
15. GA 40-412
16. GA 40A412
17. NACA64-512 a=0.5
18. NACA65-512 a=0.6
19. NACA66-510 a=0.5
20. NACA65-510 a=0.6
21. NACA64-512 a=0.6