Similarly shaped airfoils to NACA63-517 a=0.6
New! Bulk download of polars in Excel format: NACA63-517%20a%3D0.6.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. NACA64-517 a=0.6
3. GA 35-417
4. NACA64-517 a=0.5
5. GA 37-417
6. NACA63-517 a=0.8
7. NACA63-518 a=0.6
8. NACA63-516 a=0.6
9. NACA64-517 a=0.8
10. NACA63-516 a=0.5
11. NACA63-617
12. NACA64-516 a=0.6
13. NACA63-518 a=0.5
14. NACA64-518 a=0.6
15. GA 35-416
16. NACA64-516 a=0.5
17. NACA64-617
18. GA 35-418
19. NACA64-518 a=0.5
20. GA 37-416
21. NACA63-518 a=0.8