Similarly shaped airfoils to NACA65-411 a=0.6
New! Bulk download of polars in Excel format: NACA65-411%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. GA 40-311
3. GA 40A311
4. NACA64-411 a=0.6
5. NACA65-411 a=0.8
6. GA 37A311
7. NACA64-411 a=0.5
8. NACA65-511
9. NACA64A411
10. GA 35A311
11. NACA63-411 a=0.6
12. NACA63A411
13. NACA64-411 a=0.8
14. NACA65A411
15. GA 37-311
16. NACA65-412 a=0.6
17. NACA65-410 a=0.6
18. NACA63-411 a=0.5
19. NACA66-411 a=0.6
20. GOE 673
21. NACA64-511