Similarly shaped airfoils to NACA66-714 a=0.8
New! Bulk download of polars in Excel format: NACA66-714%20a%3D0.8.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. NACA65A714
3. NACA66-715 a=0.8
4. NACA66-713 a=0.8
5. NACA66A713
6. NACA66A715
7. NACA65A715
8. NACA67-714 a=0.8
9. NACA67-713 a=0.8
10. NACA66-714 a=0.6
11. NACA67A713
12. NACA67A714
13. NACA65-714 a=0.8
14. NACA65-715 a=0.8
15. NACA66-614 a=0.8
16. NACA65A713
17. EPPLER 668
18. EPPLER 433
19. NACA64A714
20. NACA66-614 a=0.6
21. NACA66A614