Similarly shaped airfoils to NACA63-610 a=0.0
New! Bulk download of polars in Excel format: NACA63-610%20a%3D0.0.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. NACA63-610 a=0.2
3. NACA63-510 a=0.2
4. NACA64-610 a=0.2
5. NACA64-510 a=0.2
6. NACA65-610 a=0.0
7. NACA63-611 a=0.0
8. NACA63-609 a=0.0
9. NACA64-609 a=0.0
10. NACA64-611 a=0.0
11. NACA65-510 a=0.2
12. NACA65-610 a=0.2
13. NACA63-611 a=0.2
14. NACA63-510 a=0.5
15. NACA63-509 a=0.2
16. NACA64-611 a=0.2
17. NACA65-609 a=0.0
18. NACA63-710 a=0.0
19. NACA63-510 a=0.0
20. NACA64-509 a=0.2
21. NACA64-510 a=0.0