Similarly shaped airfoils to NACA63-714 a=0.6
New! Bulk download of polars in Excel format: NACA63-714%20a%3D0.6.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. NACA63-714 a=0.5
3. NACA64-714 a=0.5
4. GA 35-614
5. GA 37-614
6. NACA63-715 a=0.6
7. NACA63-713 a=0.6
8. NACA64-713 a=0.6
9. NACA64-715 a=0.6
10. NACA63-713 a=0.5
11. NACA63-715 a=0.5
12. NACA63-714 a=0.8
13. NACA64-713 a=0.5
14. NACA65-714 a=0.6
15. GA 35A614
16. GA 35-615
17. NACA64-715 a=0.5
18. GOE 758
19. GOE 549
20. NACA64-714 a=0.8
21. GOE 426