Similarly shaped airfoils to NACA63-718 a=0.6
New! Bulk download of polars in Excel format: NACA63-718%20a%3D0.6.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. NACA63-718 a=0.5
3. GA 35-618
4. NACA64-718 a=0.5
5. GA 37-618
6. NACA63-719 a=0.6
7. NACA63-717 a=0.6
8. NACA64-717 a=0.6
9. NACA64-719 a=0.6
10. NACA63-717 a=0.5
11. NACA63-719 a=0.5
12. NACA63-718 a=0.8
13. NACA64-717 a=0.5
14. GA 35-617
15. GA 35-619
16. NACA64-718 a=0.8
17. NACA64-719 a=0.5
18. FX 84-W-175
19. GA 37-617
20. NACA63-618 a=0.6
21. GA 37-619