Similarly shaped airfoils to NACA65A618
New! Bulk download of polars in Excel format: NACA65A618.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. NACA66-618 a=0.8
3. NACA66A618
4. NACA65A619
5. NACA65A617
6. NACA66-718
7. NACA65-618 a=0.8
8. NACA64A619
9. NACA66A617
10. NACA66-617 a=0.8
11. NACA65-718
12. NACA65-619 a=0.8
13. NACA66-717
14. NACA65A518
15. NACA65A718
16. NACA65-719
17. NACA63A618
18. NACA66-618 a=0.6
19. NACA64A718
20. NACA66A718
21. NACA65-618 a=0.6