Similarly shaped airfoils to NACA64-415
New! Bulk download of polars in Excel format: NACA64-415.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (40) | 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. NACA63-415
3. NACA63-315 a=0.8
4. NACA64-315 a=0.6
5. NACA63-315 a=0.6
6. NACA64(2)-415
7. GA 37-215
8. NACA65-415
9. NACA64-315 a=0.5
10. GA 35-215
11. NACA63A315
12. NACA65-315 a=0.8
13. EM CY 1016 20145
14. NACA64-415 a=0.8
15. NACA64-416
16. NACA64-414
17. NACA63-315 a=0.5
18. NACA63A314
19. NACA64-314 a=0.8
20. NACA64-315
21. NACA64A315