Similarly shaped airfoils to NACA66-614 a=0.0
New! Bulk download of polars in Excel format: NACA66-614%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. NACA66-614 a=0.2
3. NACA66-615 a=0.0
4. NACA66-613 a=0.0
5. NACA66-514 a=0.0
6. NACA66-714 a=0.0
7. NACA66-615 a=0.2
8. NACA66-513 a=0.2
9. NACA67-614 a=0.0
10. NACA67-613 a=0.0
11. NACA66-514 a=0.5
12. NACA66-515 a=0.2
13. NACA66-613 a=0.2
14. NACA67-614 a=0.2
15. AH 88-K-136/16
16. NACA65-614 a=0.0
17. NACA67-513 a=0.2
18. AH 93-K-132/15
19. NACA67-613 a=0.2
20. NACA65-615 a=0.0
21. NACA67-514 a=0.2