Similarly shaped airfoils to NACA63-711 a=0.6
New! Bulk download of polars in Excel format: NACA63-711%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. NACA63-711 a=0.5
3. NACA64-711 a=0.5
4. NACA65-711 a=0.6
5. NACA63-712 a=0.6
6. NACA63-710 a=0.6
7. NACA64-710 a=0.6
8. GA 35-611
9. NACA64-712 a=0.6
10. GA 37-611
11. NACA65-711 a=0.5
12. NACA63-710 a=0.5
13. NACA64-710 a=0.5
14. NACA63-712 a=0.5
15. GA 35A611
16. NACA63-711 a=0.8
17. NACA65-710 a=0.6
18. NACA64-712 a=0.5
19. NACA64-711 a=0.8
20. GA 37A611
21. GOE 477