Similarly shaped airfoils to NACA65-509 a=0.5
New! Bulk download of polars in Excel format: NACA65-509%20a%3D0.5.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. NACA64-509 a=0.5
3. NACA64-509 a=0.6
4. NACA63-509 a=0.5
5. NACA66-509 a=0.5
6. NACA63-509 a=0.6
7. NACA66-509 a=0.6
8. NACA64-510 a=0.5
9. NACA65-510 a=0.5
10. GA 40-410
11. NACA64-510 a=0.6
12. GA 40A410
13. NACA65-510 a=0.6
14. GA 37-410
15. NACA65-609 a=0.0
16. NACA65-609 a=0.2
17. NACA63-510 a=0.5
18. GA 37A410
19. NACA65-509 a=0.8
20. NACA63-510 a=0.6
21. SD6080 (9.2%)