Similarly shaped airfoils to NACA64-714 a=0.8


Direct link: NACA64-714 a=0.8
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.

1. NACA63-714 a=0.8
2. NACA63A714
3. NACA65-714 a=0.8
4. NACA64A714
5. NACA63A713
6. NACA64-715 a=0.8
7. NACA64-713 a=0.8
8. NACA63-713 a=0.8
9. NACA64A713
10. NACA63-715 a=0.8
11. NACA65-713 a=0.8
12. NACA64-714 a=0.6
13. NACA63-714 a=0.6
14. NACA64-614 a=0.8
15. EPPLER 210
16. NACA63-614 a=0.8
17. GA 37-614
18. NACA65-715 a=0.8
19. FX 84-W-140
20. NACA65-714 a=0.6
21. NACA65-614 a=0.8