Similarly shaped airfoils to NACA64-120 a=0.6
New! Bulk download of polars in Excel format: NACA64-120%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. NACA64-120 a=0.8
3. NACA64-120
4. NACA64-120 a=0.2
5. NACA64-120 a=0.0
6. NACA63-120 a=0.6
7. NACA63-120 a=0.5
8. NACA63-120 a=0.8
9. NACA63-120
10. NACA63-120 a=0.2
11. NACA64-220 a=0.0
12. NACA63-120 a=0.0
13. NACA64-220
14. NACA64-220 a=0.2
15. NACA63-220 a=0.0
16. NACA64-119 a=0.6
17. NACA64-119 a=0.5
18. NACA64-119 a=0.8
19. NACA63-220
20. NACA64-119
21. NACA64-119 a=0.2