Similarly shaped airfoils to NACA67-513 a=0.0
New! Bulk download of polars in Excel format: NACA67-513%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. NACA67-413 a=0.2
3. NACA67-413 a=0.5
4. NACA67-514 a=0.0
5. NACA66-513 a=0.0
6. NACA67-512 a=0.0
7. NACA67-413 a=0.0
8. NACA67-613 a=0.0
9. NACA67-514 a=0.2
10. NACA66-514 a=0.0
11. NACA67-412 a=0.2
12. NACA66-513 a=0.2
13. NACA67-512 a=0.2
14. NACA66-413 a=0.2
15. NACA67-413 a=0.6
16. NACA66-514 a=0.2
17. NACA67-414 a=0.2
18. NACA66-414 a=0.2
19. NACA67-414 a=0.5
20. NACA67-412 a=0.5
21. NACA66-413 a=0.5