Similarly shaped airfoils to NACA63-715 a=0.6
New! Bulk download of polars in Excel format: NACA63-715%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. NACA63-715 a=0.5
3. NACA64-715 a=0.5
4. GA 35-615
5. GA 37-615
6. NACA63-716 a=0.6
7. NACA63-714 a=0.6
8. NACA64-714 a=0.6
9. NACA64-716 a=0.6
10. NACA63-714 a=0.5
11. NACA63-716 a=0.5
12. NACA63-715 a=0.8
13. NACA64-714 a=0.5
14. GA 35-616
15. GA 35A615
16. NACA64-716 a=0.5
17. NACA64-715 a=0.8
18. NACA65-715 a=0.6
19. GA 35-614
20. GA 37-616
21. GA 37-614