Similarly shaped airfoils to NACA66-713 a=0.5
New! Bulk download of polars in Excel format: NACA66-713%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. NACA66-714 a=0.5
3. NACA66-712 a=0.5
4. NACA67-713 a=0.5
5. NACA67-712 a=0.5
6. NACA66-714 a=0.6
7. NACA65-713 a=0.5
8. NACA66-712 a=0.6
9. NACA67-713 a=0.6
10. NACA65-714 a=0.5
11. NACA67-712 a=0.6
12. NACA65-713 a=0.6
13. NACA66-613 a=0.5
14. NACA65-714 a=0.6
15. NACA66-613 a=0.6
16. GA 40A614
17. GA 40A613
18. GA 40-614
19. GA 40-613
20. EPPLER 434
21. GA 37A613