Similarly shaped airfoils to NACA63-518 a=0.5
New! Bulk download of polars in Excel format: NACA63-518%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. NACA64-518 a=0.5
3. NACA64-518 a=0.6
4. GA 35-418
5. GA 37-418
6. NACA63-519 a=0.5
7. NACA63-517 a=0.5
8. NACA63-519 a=0.6
9. NACA63-517 a=0.6
10. NACA64-517 a=0.5
11. NACA64-519 a=0.5
12. NACA63-618 a=0.2
13. NACA64-519 a=0.6
14. GA 35-417
15. NACA64-517 a=0.6
16. NACA64-618 a=0.2
17. NACA63-518 a=0.8
18. NACA63-618 a=0.0
19. GA 35-419
20. GA 35-318
21. GA 37-417