Similarly shaped airfoils to NACA64-717 a=0.6
New! Bulk download of polars in Excel format: NACA64-717%20a%3D0.6.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. NACA64-717 a=0.5
3. GA 37-617
4. NACA63-717 a=0.5
5. GA 35-617
6. NACA64-718 a=0.6
7. NACA64-716 a=0.6
8. NACA65-717 a=0.6
9. NACA63-716 a=0.6
10. NACA63-718 a=0.6
11. NACA64-716 a=0.5
12. NACA65-717 a=0.5
13. NACA64-718 a=0.5
14. NACA64-717 a=0.8
15. GA 35A617
16. NACA63-716 a=0.5
17. NACA65-716 a=0.6
18. GA 35A616
19. GA 37-616
20. GA 37-618
21. NACA63-718 a=0.5