Similarly shaped airfoils to NACA65-714 a=0.0
New! Bulk download of polars in Excel format: NACA65-714%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
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2. NACA65-714 a=0.2
3. NACA64-714 a=0.0
4. NACA65-715 a=0.0
5. NACA65-713 a=0.0
6. NACA64-714 a=0.2
7. NACA64-614 a=0.2
8. NACA65-613 a=0.2
9. NACA65-614 a=0.0
10. NACA64-715 a=0.0
11. NACA65-615 a=0.2
12. NACA65-715 a=0.2
13. NACA63-714 a=0.0
14. NACA64-715 a=0.2
15. NACA66-713 a=0.0
16. AH 79-K-132/20
17. NACA65-713 a=0.2
18. NACA66-714 a=0.0
19. NACA66-613 a=0.2
20. NACA63-714 a=0.2
21. NACA64-615 a=0.2