Similarly shaped airfoils to NACA64A111
New! Bulk download of polars in Excel format: NACA64A111.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. NACA65-111 a=0.8
3. NACA65-111 a=0.6
4. NACA65-111
5. NACA65-111 a=0.5
6. NACA65A111
7. NACA65-111 a=0.2
8. NACA65-111 a=0.0
9. NACA64-111 a=0.8
10. NACA64-111 a=0.6
11. NACA64-111
12. NACA64-111 a=0.5
13. NACA64-111 a=0.2
14. NACA64-111 a=0.0
15. NACA63-111 a=0.8
16. NACA63-111 a=0.6
17. NACA63-111
18. NACA63-111 a=0.5
19. NACA64-112 a=0.8
20. NACA63-111 a=0.2
21. NACA64(1)-112