Similarly shaped airfoils to NACA64-516 a=0.8
New! Bulk download of polars in Excel format: NACA64-516%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. NACA63-516 a=0.8
3. NACA63-616
4. NACA64-516 a=0.6
5. NACA63A516
6. NACA63A515
7. NACA65-516 a=0.8
8. NACA63-516 a=0.6
9. NACA64-517 a=0.8
10. NACA64-515 a=0.8
11. NACA65-616
12. NACA64-617
13. NACA64-615
14. NACA64-716
15. NACA64A516
16. NACA63-515 a=0.8
17. NACA63-517 a=0.8
18. GA 37-416
19. FX 60-160
20. NACA64A515
21. NACA63-615