Similarly shaped airfoils to NACA65-619 a=0.0
New! Bulk download of polars in Excel format: NACA65-619%20a%3D0.0.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. NACA65-619 a=0.2
3. NACA65-620 a=0.0
4. NACA65-618 a=0.0
5. NACA65-519 a=0.0
6. NACA65-518 a=0.2
7. NACA65-719 a=0.0
8. NACA65-620 a=0.2
9. NACA65-520 a=0.2
10. NACA64-619 a=0.0
11. NACA65-519 a=0.5
12. NACA64-619 a=0.2
13. NACA65-618 a=0.2
14. NACA64-620 a=0.2
15. NACA64-620 a=0.0
16. NACA65-518 a=0.0
17. NACA65-720 a=0.0
18. NACA64-719 a=0.0
19. NACA64-519 a=0.2
20. NACA65-419 a=0.5
21. NACA64-720 a=0.0