Similarly shaped airfoils to NACA64-212 a=0.6
New! Bulk download of polars in Excel format: NACA64-212%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. NACA63-212 a=0.6
3. NACA64-212 a=0.8
4. NACA63-212 a=0.5
5. NACA63-212 a=0.8
6. NACA64(1)-212
7. NACA64-212 a=0.2
8. NACA64-212
9. NACA64-312
10. NACA65-212 a=0.6
11. NACA65-212 a=0.5
12. NACA63A212
13. NACA63-212 a=0.2
14. NACA63-212
15. NACA63-312
16. NACA65-212 a=0.8
17. HQ 1.0/12
18. NACA64A212
19. NACA64-212 a=0.0
20. NACA65(1)-212 a=0.6
21. NACA64-312 a=0.0