Similarly shaped airfoils to NACA64-617 a=0.8
New! Bulk download of polars in Excel format: NACA64-617%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
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. NACA64-717
3. NACA63-717
4. NACA64-618 a=0.8
5. NACA64-616 a=0.8
6. NACA63A617
7. NACA63A616
8. NACA64-617 a=0.6
9. NACA65-617 a=0.8
10. NN7 MK20
11. NACA63-616 a=0.8
12. NACA63-618 a=0.8
13. NACA64-716
14. NACA64-718
15. NACA64A617
16. NACA65-717
17. NACA63-617 a=0.6
18. NACA64A616
19. NACA63-716
20. NACA63-718
21. NACA65-616 a=0.8