Similarly shaped airfoils to NACA65-714 a=0.8
New! Bulk download of polars in Excel format: NACA65-714%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
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2. NACA63A714
3. NACA64-714 a=0.8
4. NACA65A714
5. NACA65-715 a=0.8
6. NACA65-713 a=0.8
7. NACA65A713
8. NACA64A713
9. NACA63A713
10. NACA64-715 a=0.8
11. NACA65-714 a=0.6
12. NACA63-714 a=0.8
13. EPPLER 668
14. NACA64A715
15. NACA66A713
16. NACA66-713 a=0.8
17. NACA66-714 a=0.8
18. NACA66A714
19. NACA65-614 a=0.8
20. NACA63A715
21. NACA64-713 a=0.8