Similarly shaped airfoils to NACA65-619 a=0.6
New! Bulk download of polars in Excel format: NACA65-619%20a%3D0.6.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. NACA65-620 a=0.6
3. NACA65-618 a=0.6
4. NACA65-619 a=0.8
5. NACA65-618 a=0.5
6. NACA65-620 a=0.5
7. NACA64-619 a=0.6
8. NACA64A619
9. GA 40-419
10. NACA65-719
11. GA 40A419
12. NACA64-619 a=0.5
13. NACA65-519 a=0.6
14. NACA65-719 a=0.5
15. NACA65-719 a=0.6
16. NACA64-620 a=0.6
17. NACA65-620 a=0.8
18. NACA65-618 a=0.8
19. GA 40-619
20. GA 40A619
21. NACA63A619