Similarly shaped airfoils to NACA65-716 a=0.5
New! Bulk download of polars in Excel format: NACA65-716%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. GA 40-616
3. GA 40A616
4. GA 37A616
5. NACA64-716 a=0.5
6. NACA65-717 a=0.5
7. NACA65-715 a=0.5
8. GA 35A616
9. NACA64-716 a=0.6
10. NACA65-717 a=0.6
11. GA 40-617
12. GA 37-616
13. GA 40A617
14. NACA65-715 a=0.6
15. GA 40A615
16. GA 40-615
17. NACA64-717 a=0.5
18. GA 37A615
19. NACA64-717 a=0.6
20. GA 37-617
21. GA 35A615