Similarly shaped airfoils to NACA64-510 a=0.8
New! Bulk download of polars in Excel format: NACA64-510%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. NACA64-610
3. NACA63-610
4. NACA63A510
5. NACA65-510 a=0.8
6. NACA64A510
7. NACA65-610
8. HQ 3.0/10
9. NACA64-510 a=0.6
10. NACA63A509
11. EM J8 3010 DrW
12. NACA63-510 a=0.6
13. NACA64A509
14. NACA64-511 a=0.8
15. NACA64-509 a=0.8
16. EM J19 3010
17. NACA65-509 a=0.8
18. NACA63-509 a=0.8
19. NACA63-511 a=0.8
20. NACA65-510 a=0.6
21. NACA64-611