Similarly shaped airfoils to NACA66-719 a=0.8
New! Bulk download of polars in Excel format: NACA66-719%20a%3D0.8.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. NACA66-720 a=0.8
3. NACA66-718 a=0.8
4. NACA66A718
5. NACA66A720
6. NACA65A719
7. NACA66-719 a=0.6
8. NACA65A720
9. NACA66-619 a=0.8
10. NACA66A619
11. NACA66-619 a=0.6
12. NACA67-718 a=0.8
13. NACA67A718
14. NACA66-720 a=0.6
15. NACA66-718 a=0.6
16. NACA66-618 a=0.8
17. NACA65A718
18. NACA65A619
19. NACA67-719 a=0.8
20. NACA66-719 a=0.5
21. NACA67A719