Similarly shaped airfoils to NACA66A614
New! Bulk download of polars in Excel format: NACA66A614.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. NACA66-714
3. NACA65A614
4. NACA66A615
5. NACA66-615 a=0.8
6. NACA66A613
7. NACA66-613 a=0.8
8. NACA66-614 a=0.6
9. NACA66-713
10. NACA66-715
11. NACA65A615
12. NACA67A614
13. NACA67-614 a=0.8
14. NACA67A613
15. NACA67-613 a=0.8
16. NACA66-514 a=0.8
17. FX 74-130 WP1
18. NACA67-714
19. NACA67-713
20. NACA66-514 a=0.6
21. NACA65-614 a=0.8