Similarly shaped airfoils to NACA64-118 a=0.6


Direct link: NACA64-118 a=0.6
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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1. NACA64-118 a=0.5
2. NACA64-118 a=0.8
3. NACA64-118
4. NACA64-118 a=0.2
5. NACA64-118 a=0.0
6. NACA63-118 a=0.6
7. NACA63-118 a=0.5
8. NACA63-118 a=0.8
9. NACA63-118
10. NACA63-118 a=0.2
11. NACA63-118 a=0.0
12. NACA64-218 a=0.0
13. NACA64-218
14. NACA63-218 a=0.0
15. NACA64-218 a=0.2
16. NACA63-218
17. NACA64-119 a=0.6
18. NACA64-117 a=0.6
19. NACA64-117 a=0.5
20. NACA64-119 a=0.5
21. NACA64-119 a=0.8