Similarly shaped airfoils to NACA64-613 a=0.8
New! Bulk download of polars in Excel format: NACA64-613%20a%3D0.8.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. NACA64-713
3. NACA63-713
4. NACA63A613
5. NACA65-613 a=0.8
6. NACA64A613
7. NACA63A612
8. NACA65-713
9. NACA64-614 a=0.8
10. NACA64-612 a=0.8
11. HQ 3.5/13
12. NACA64A612
13. NACA64-613 a=0.6
14. NACA63-612 a=0.8
15. NACA63-614 a=0.8
16. NACA65-612 a=0.8
17. NACA63-613 a=0.6
18. NACA64-712
19. NACA64-714
20. NACA63-712
21. NACA65-712