Similarly shaped airfoils to NACA66-409 a=0.6
New! Bulk download of polars in Excel format: NACA66-409%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. NACA66-409 a=0.8
3. NACA67-409 a=0.6
4. NACA66A409
5. NACA67-409 a=0.5
6. NACA66-509
7. NACA65-409 a=0.6
8. NACA65A409
9. NACA65-409 a=0.5
10. NACA67-409 a=0.8
11. NACA67A409
12. NACA66-410 a=0.6
13. NACA65-410 a=0.6
14. NACA65-409 a=0.8
15. NACA66-410 a=0.5
16. NACA65-410 a=0.5
17. DP2.47/9.48_DS
18. NACA65-509
19. NACA64A409
20. NACA66-509 a=0.0
21. NACA66-410 a=0.8