Similarly shaped airfoils to NACA64-614 a=0.5
New! Bulk download of polars in Excel format: NACA64-614%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. NACA64-614 a=0.6
3. NACA63-614 a=0.6
4. NACA65-614 a=0.5
5. NACA64-615 a=0.5
6. NACA64-613 a=0.5
7. NACA65-614 a=0.6
8. NACA63-613 a=0.5
9. NACA63-615 a=0.5
10. NACA64-615 a=0.6
11. NACA65-613 a=0.5
12. GA 37-614
13. NACA64-613 a=0.6
14. FX 84-W-140
15. NACA63-615 a=0.6
16. FX 84-W-127
17. NACA63-613 a=0.6
18. GA 35-614
19. AH 93-W-145
20. NACA64-714 a=0.2
21. NACA65-613 a=0.6