Similarly shaped airfoils to NACA64-510 a=0.6
New! Bulk download of polars in Excel format: NACA64-510%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. NACA64-510 a=0.5
3. NACA63-510 a=0.5
4. NACA65-510 a=0.6
5. GA 37-410
6. NACA65-510 a=0.5
7. GA 35-410
8. GA 35A410
9. GA 40-410
10. GA 40A410
11. GA 37A410
12. S3024 9.84%
13. NACA64-510 a=0.8
14. EPPLER E193gU-K24
15. NACA63-510 a=0.8
16. EPPLER 193
17. NACA64-511 a=0.6
18. NACA64-509 a=0.6
19. NACA65-509 a=0.6
20. NACA63-509 a=0.6
21. NACA63-511 a=0.6