Similarly shaped airfoils to NACA64-610 a=0.6
New! Bulk download of polars in Excel format: NACA64-610%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. NACA64-610 a=0.5
3. NACA65-610 a=0.6
4. NACA63-610 a=0.5
5. GA 37-610
6. NACA65-610 a=0.5
7. GA 35-610
8. GA 35A610
9. GA 40-610
10. GA 40A610
11. GA 37A610
12. DAE-51
13. NACA64-611 a=0.6
14. NACA64-609 a=0.6
15. MH 38 9.68%
16. NACA65-609 a=0.6
17. NACA63-609 a=0.6
18. NACA64-610 a=0.8
19. NACA63-611 a=0.6
20. MH 116 9.84%
21. PSU 94-097 (AIAA 2001-2478)