Similarly shaped airfoils to NACA64-517 a=0.5
New! Bulk download of polars in Excel format: NACA64-517%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. NACA63-517 a=0.5
3. GA 37-417
4. NACA63-517 a=0.6
5. GA 35-417
6. NACA64-518 a=0.5
7. NACA64-516 a=0.5
8. NACA65-517 a=0.5
9. NACA64-518 a=0.6
10. NACA63-516 a=0.5
11. NACA63-518 a=0.5
12. NACA64-516 a=0.6
13. NACA64-617 a=0.2
14. GA 35A417
15. NACA65-517 a=0.6
16. GA 37-416
17. NACA63-518 a=0.6
18. GA 35A416
19. NACA63-516 a=0.6
20. NACA64-517 a=0.8
21. NACA63-617 a=0.2