Similarly shaped airfoils to NACA67-513 a=0.2
New! Bulk download of polars in Excel format: NACA67-513%20a%3D0.2.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. NACA67-613 a=0.0
3. NACA67-413 a=0.5
4. NACA67-514 a=0.2
5. NACA66-513 a=0.2
6. NACA67-512 a=0.2
7. NACA67-512 a=0.0
8. NACA66-513 a=0.0
9. NACA66-514 a=0.2
10. NACA67-614 a=0.0
11. NACA67-413 a=0.2
12. NACA67-613 a=0.2
13. NACA67-514 a=0.0
14. NACA67-513 a=0.5
15. NACA67-413 a=0.6
16. NACA66-613 a=0.0
17. NACA66-514 a=0.0
18. NACA67-612 a=0.0
19. NACA66-614 a=0.0
20. NACA67-412 a=0.5
21. NACA66-413 a=0.5