Similarly shaped airfoils to NACA63-118 a=0.5
New! Bulk download of polars in Excel format: NACA63-118%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. NACA63-118 a=0.8
3. NACA63-118 a=0.2
4. NACA63-118
5. NACA63-118 a=0.0
6. NACA64-118 a=0.5
7. NACA64-118 a=0.6
8. NACA64-118 a=0.8
9. NACA64-118 a=0.2
10. NACA64-118
11. NACA64-118 a=0.0
12. NACA63-218 a=0.0
13. NACA64-218 a=0.0
14. NACA63-218
15. NACA63-218 a=0.2
16. NACA64-218
17. NACA63-119 a=0.5
18. NACA63-117 a=0.5
19. NACA63-119 a=0.6
20. NACA63-117 a=0.6
21. NACA63-119 a=0.8