Similarly shaped airfoils to NACA63-717
New! Bulk download of polars in Excel format: NACA63-717.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. NACA63-617 a=0.8
3. NACA64-617 a=0.8
4. NN7 MK20
5. NACA63-718
6. NACA63-716
7. NACA63-517 a=0.8
8. NACA63-617
9. NACA64-716
10. NACA63(3)-618
11. NACA63-618 a=0.8
12. NACA64-718
13. NACA63-616 a=0.8
14. NACA64(3)-618
15. NACA64-517 a=0.8
16. NACA64-618 a=0.8
17. NACA64-616 a=0.8
18. NACA64-617
19. NACA63(420)-517
20. GA 35-417
21. FX 61-168