Similarly shaped airfoils to NACA64-111 a=0.0
New! Bulk download of polars in Excel format: NACA64-111%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. NACA63-111 a=0.0
3. NACA63-111 a=0.2
4. NACA64-111 a=0.5
5. NACA64-111
6. NACA64-111 a=0.6
7. NACA63-111 a=0.5
8. NACA64-111 a=0.8
9. NACA63-111
10. NACA63-111 a=0.6
11. NACA63-111 a=0.8
12. NACA65-111 a=0.0
13. NACA65-111 a=0.2
14. NACA63A111
15. NACA65-111 a=0.5
16. NACA65-111
17. NACA65-111 a=0.6
18. NACA65-111 a=0.8
19. NACA64A111
20. NACA64-112 a=0.0
21. NACA64-110 a=0.0