Similarly shaped airfoils to NACA65-711 a=0.2
New! Bulk download of polars in Excel format: NACA65-711%20a%3D0.2.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. NACA65-711 a=0.0
3. NACA63-711 a=0.2
4. NACA65-712 a=0.2
5. NACA65-710 a=0.2
6. NACA66-711 a=0.2
7. NACA64-711 a=0.0
8. NACA64-712 a=0.2
9. NACA66-710 a=0.2
10. NACA65-710 a=0.0
11. NACA63-711 a=0.0
12. NACA66-711 a=0.0
13. NACA66-710 a=0.0
14. NACA65-611 a=0.2
15. NACA63-712 a=0.2
16. NACA65-611 a=0.5
17. NACA64-710 a=0.2
18. NACA65-712 a=0.0
19. GA 40-611
20. GA 40A611
21. NACA64-712 a=0.0