Similarly shaped airfoils to NACA65-411 a=0.2
New! Bulk download of polars in Excel format: NACA65-411%20a%3D0.2.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=0.2
3. NACA65-511 a=0.0
4. GA 40-311
5. NACA64-411 a=0.0
6. GA 40A311
7. EPPLER 374
8. GA 37A311
9. NACA63-411 a=0.2
10. NACA64-511 a=0.0
11. NACA65-311 a=0.5
12. NACA65-412 a=0.2
13. NACA65-410 a=0.2
14. GA 35A311
15. NACA65-411 a=0.5
16. NACA66-411 a=0.2
17. MH 18 11.16%
18. NACA64-412 a=0.2
19. NACA63-411 a=0.0
20. NACA65-410 a=0.0
21. EPPLER 220