Similarly shaped airfoils to NACA63-715 a=0.5
New! Bulk download of polars in Excel format: NACA63-715%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
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2. NACA63-715 a=0.6
3. GA 35-615
4. NACA64-715 a=0.6
5. GA 37-615
6. NACA63-716 a=0.5
7. NACA63-714 a=0.5
8. NACA64-714 a=0.5
9. NACA64-716 a=0.5
10. GA 35-616
11. NACA63-716 a=0.6
12. GA 35A615
13. NACA63-714 a=0.6
14. NACA64-716 a=0.6
15. GA 37-616
16. GA 35-614
17. NACA64-714 a=0.6
18. GA 37-614
19. GA 35A614
20. NACA65-715 a=0.5
21. GA 30-614