Similarly shaped airfoils to NACA65A714
New! Bulk download of polars in Excel format: NACA65A714.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. NACA66A714
3. NACA66-714 a=0.8
4. NACA65-714 a=0.8
5. NACA65A715
6. NACA65A713
7. NACA63A714
8. NACA65-715 a=0.8
9. EPPLER 668
10. NACA64A715
11. NACA66A713
12. NACA66-713 a=0.8
13. EPPLER 433
14. NACA65A614
15. NACA63A715
16. NACA64A713
17. NACA66-614 a=0.8
18. NACA66A715
19. NACA66-715 a=0.8
20. NACA65-614 a=0.8
21. NACA66-714 a=0.6