Similarly shaped airfoils to NACA64-515 a=0.5
New! Bulk download of polars in Excel format: NACA64-515%20a%3D0.5.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. NACA64-515 a=0.6
3. GA 37-415
4. NACA63-515 a=0.6
5. GA 35-415
6. NACA65-515 a=0.5
7. GA 35A415
8. NACA64-516 a=0.5
9. NACA64-514 a=0.5
10. GA 40-415
11. NACA65-515 a=0.6
12. GA 40A415
13. GA 37A415
14. NACA64-516 a=0.6
15. NACA63-514 a=0.5
16. GA 35A414
17. NACA63-516 a=0.5
18. NACA65(2)-415 a=0.5
19. GA 37-416
20. NACA64-514 a=0.6
21. NACA64-615 a=0.2