Similarly shaped airfoils to NACA64-619 a=0.5
New! Bulk download of polars in Excel format: NACA64-619%20a%3D0.5.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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA63-619 a=0.5
3. NACA63-619 a=0.6
4. NACA64-620 a=0.5
5. NACA64-618 a=0.5
6. NACA64-620 a=0.6
7. GA 37-419
8. NACA63-618 a=0.5
9. NACA63-620 a=0.5
10. NACA64-618 a=0.6
11. GA 35-419
12. NACA65-619 a=0.5
13. NACA63-620 a=0.6
14. NACA64-719 a=0.2
15. NACA63-618 a=0.6
16. NACA64-519 a=0.6
17. NACA64-519 a=0.5
18. NACA64-719 a=0.5
19. NACA65-618 a=0.5
20. NACA63-519 a=0.5
21. NACA65-619 a=0.6