Similarly shaped airfoils to NACA67-614
New! Bulk download of polars in Excel format: NACA67-614.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. NACA67-514 a=0.8
3. NACA67-514 a=0.6
4. NACA67-615
5. NACA67-613
6. NACA67A513
7. NACA67-714
8. NACA67A515
9. NACA67-513 a=0.8
10. NACA67-515 a=0.8
11. NACA66-614
12. NACA66A514
13. NACA66-514 a=0.8
14. NACA66-615
15. NACA67-414 a=0.8
16. NACA66A515
17. NACA66-515 a=0.8
18. NACA67A614
19. NACA67-514 a=0.5
20. NACA67A414
21. NACA67-414 a=0.6