Similarly shaped airfoils to NACA63-617 a=0.8
New! Bulk download of polars in Excel format: NACA63-617%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. NACA63-717
3. NACA64-717
4. NACA63-618 a=0.8
5. NACA63-616 a=0.8
6. NACA63-617 a=0.6
7. NACA64-616 a=0.8
8. NACA64-618 a=0.8
9. NACA63-716
10. NACA63-718
11. NACA64-617 a=0.6
12. NN7 MK20
13. NACA64-716
14. NACA64-718
15. NACA63A616
16. NACA63A617
17. NACA63(3)-618
18. NACA63-517 a=0.8
19. NACA63-717 a=0.8
20. NACA64-717 a=0.8
21. NACA64(3)-618