Similarly shaped airfoils to NACA66-714 a=0.6
New! Bulk download of polars in Excel format: NACA66-714%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. NACA66-715 a=0.6
3. NACA66-713 a=0.6
4. NACA67-714 a=0.6
5. NACA67-713 a=0.6
6. NACA66-714 a=0.8
7. NACA66-713 a=0.5
8. NACA66-715 a=0.5
9. NACA66A714
10. NACA65-714 a=0.6
11. NACA67-713 a=0.5
12. NACA67-714 a=0.5
13. NACA65-715 a=0.6
14. FX 67-K-150/17
15. NACA66-614 a=0.6
16. NACA65-714 a=0.5
17. NACA65A714
18. NACA65-715 a=0.5
19. NACA66-713 a=0.8
20. NACA66-715 a=0.8
21. NACA66A713