Similarly shaped airfoils to NACA63(3)-018
New! Bulk download of polars in Excel format: NACA63%283%29-018.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. GA 35-018
3. NACA64-018
4. GA 37-018
5. NACA63-118 a=0.0
6. NACA63-118
7. NACA63-118 a=0.2
8. NACA64-118 a=0.0
9. GA 35-017
10. NACA64-118
11. NACA64-118 a=0.2
12. GA 35-019
13. EPPLER 476
14. NACA63-118 a=0.8
15. GA 37-017
16. NACA63-118 a=0.5
17. NACA63-118 a=0.6
18. NACA64-118 a=0.8
19. NACA64-118 a=0.5
20. NACA63-119 a=0.0
21. NACA64-118 a=0.6