Similarly shaped airfoils to NACA63-112 a=0.6
New! Bulk download of polars in Excel format: NACA63-112%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. NACA63-112 a=0.8
3. NACA63-112
4. NACA64-112 a=0.6
5. NACA63-112 a=0.2
6. NACA64-112 a=0.5
7. NACA64-112 a=0.8
8. NACA64(1)-112
9. NACA63-112 a=0.0
10. NACA64-112
11. NACA64-112 a=0.2
12. NACA64-112 a=0.0
13. NACA63A112
14. NACA63-212
15. NACA63-212 a=0.0
16. NACA64-212
17. NACA64-212 a=0.0
18. NACA63-113 a=0.6
19. NACA63-111 a=0.6
20. NACA63-113 a=0.5
21. NACA63-111 a=0.5