Similarly shaped airfoils to NACA63A118
New! Bulk download of polars in Excel format: NACA63A118.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. NACA65-118 a=0.8
3. NACA65-118 a=0.6
4. NACA65-118
5. NACA65-118 a=0.5
6. NACA63A119
7. NACA63A117
8. NACA64A119
9. NACA64-118 a=0.8
10. NACA65-118 a=0.2
11. NACA64-118 a=0.6
12. NACA63A018
13. NACA64-118
14. NACA64-118 a=0.5
15. NACA64-119 a=0.8
16. GA 35A018
17. NACA65-118 a=0.0
18. NACA64-119 a=0.6
19. NACA64-119 a=0.5
20. NACA64-119
21. NACA64A117