Similarly shaped airfoils to NACA64A713
New! Bulk download of polars in Excel format: NACA64A713.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. NACA65-713 a=0.8
3. NACA65A713
4. NACA64-713 a=0.8
5. NACA64A714
6. NACA64A712
7. NACA63A712
8. NACA65A712
9. NACA64-714 a=0.8
10. NACA65-714 a=0.8
11. NACA63A714
12. NACA63-713 a=0.8
13. NACA65-613 a=0.8
14. NACA65-712 a=0.8
15. NACA63-714 a=0.8
16. NACA66A713
17. NACA64A613
18. NACA66-713 a=0.8
19. NACA65-713 a=0.6
20. NACA63A613
21. NACA66A712