Similarly shaped airfoils to NACA64A614
New! Bulk download of polars in Excel format: NACA64A614.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
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2. NACA65-614 a=0.8
3. NACA65-714
4. NACA65A614
5. NACA64-614 a=0.8
6. NACA64-714
7. NACA64A615
8. NACA64A613
9. NACA63A613
10. NACA65A613
11. NACA65-615 a=0.8
12. NACA64-615 a=0.8
13. NACA63A615
14. NACA65-715
15. NACA64-715
16. NACA63-614 a=0.8
17. EPPLER 68
18. NACA65-614 a=0.6
19. FX 75-141
20. NACA65-613 a=0.8
21. NACA65-514 a=0.8