Similarly shaped airfoils to NACA64-615 a=0.2
New! Bulk download of polars in Excel format: NACA64-615%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. NACA64-715 a=0.0
3. NACA64-615 a=0.0
4. NACA63-715 a=0.0
5. NACA63-615 a=0.0
6. NACA65-615 a=0.2
7. NACA64-616 a=0.2
8. NACA64-614 a=0.2
9. NACA65-615 a=0.0
10. NACA64-716 a=0.0
11. NACA63-614 a=0.2
12. NACA63-616 a=0.2
13. NACA64-614 a=0.0
14. NACA64-515 a=0.5
15. NACA65-715 a=0.0
16. NACA63-716 a=0.0
17. NACA65-614 a=0.2
18. NACA64-714 a=0.0
19. NACA63-614 a=0.0
20. NACA63-515 a=0.5
21. NACA65-614 a=0.0