Similarly shaped airfoils to NACA63-417 a=0.8
New! Bulk download of polars in Excel format: NACA63-417%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. NACA64-417 a=0.8
3. NACA64-517
4. NACA63-417 a=0.6
5. NACA64-417 a=0.6
6. GA 35-317
7. NACA63-417
8. NACA63-418 a=0.8
9. NACA63-416 a=0.8
10. NACA63-417 a=0.5
11. NACA63-518
12. GA 37-317
13. NACA63-516
14. NACA64-416 a=0.8
15. NACA64-418 a=0.8
16. NACA64-417 a=0.5
17. NACA64-518
18. NACA64-417
19. NACA64-516
20. NACA63(3)-418
21. NACA63-416 a=0.6