Similarly shaped airfoils to NACA66-411 a=0.0
New! Bulk download of polars in Excel format: NACA66-411%20a%3D0.0.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. NACA66-311 a=0.5
3. NACA66-311 a=0.2
4. NACA67-411 a=0.0
5. NACA67-411 a=0.2
6. NACA66-311 a=0.6
7. NACA65-411 a=0.0
8. NACA66-412 a=0.0
9. NACA67-410 a=0.0
10. NACA66-410 a=0.0
11. NACA66-412 a=0.2
12. NACA65-411 a=0.2
13. NACA67-410 a=0.2
14. NACA66-311 a=0.0
15. NACA65-412 a=0.0
16. NACA66-410 a=0.2
17. NACA66-511 a=0.0
18. NACA67-311 a=0.5
19. NACA65-412 a=0.2
20. NACA67-311 a=0.2
21. NACA66-310 a=0.2