Similarly shaped airfoils to NACA65A718
New! Bulk download of polars in Excel format: NACA65A718.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. NACA66-718 a=0.8
3. NACA66A718
4. NACA65A719
5. NACA65A717
6. NACA65-718 a=0.8
7. NACA64A719
8. NACA66A717
9. NACA66-717 a=0.8
10. NACA65-719 a=0.8
11. NACA65A618
12. NACA63A718
13. NACA64A717
14. NACA63A719
15. NACA66-718 a=0.6
16. NACA66-719 a=0.8
17. NACA65A617
18. NACA66A719
19. NACA66-618 a=0.8
20. NACA65-718 a=0.6
21. NACA65A619