Similarly shaped airfoils to NACA63-516 a=0.8
New! Bulk download of polars in Excel format: NACA63-516%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. NACA64-516 a=0.8
3. NACA64-616
4. NACA63-516 a=0.6
5. NACA64-516 a=0.6
6. NACA63-517 a=0.8
7. NACA63-515 a=0.8
8. NACA63-617
9. NACA63-615
10. NACA63-716
11. NACA64-515 a=0.8
12. GA 35-416
13. NACA64-517 a=0.8
14. NACA64-716
15. HQ 3.0/15
16. NACA64-615
17. NACA64-617
18. EM J18 3015 DrW r0,8
19. NACA63A516
20. GA 37-416
21. NACA63A515