Similarly shaped airfoils to NACA65-411 a=0.0
New! Bulk download of polars in Excel format: NACA65-411%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. NACA64-411 a=0.0
3. NACA64-411 a=0.2
4. NACA65-311 a=0.5
5. NACA65-311 a=0.2
6. EPPLER 374
7. NACA63-411 a=0.0
8. NACA65-412 a=0.0
9. NACA63-411 a=0.2
10. NACA65-410 a=0.0
11. NACA65-311 a=0.6
12. NACA66-411 a=0.0
13. GA 40-211
14. GA 40A211
15. NACA64-311 a=0.5
16. NACA64-412 a=0.0
17. NACA65-412 a=0.2
18. GA 40-311
19. GA 40A311
20. NACA64-412 a=0.2
21. SD6060-104-88