Similarly shaped airfoils to NACA64-614 a=0.8
New! Bulk download of polars in Excel format: NACA64-614%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. NACA64-714
3. NACA63-714
4. NACA63A614
5. NACA65-614 a=0.8
6. NACA64A614
7. NACA63A613
8. FX 75-141
9. NACA65-714
10. NACA64-615 a=0.8
11. NACA64-613 a=0.8
12. HQ 3.5/14
13. NACA64-614 a=0.6
14. NACA63-613 a=0.8
15. NACA64A613
16. NACA63-615 a=0.8
17. NACA63-614 a=0.6
18. NACA64-713
19. NACA65-613 a=0.8
20. NACA64-715
21. NACA63-713