Similarly shaped airfoils to NACA63-718
New! Bulk download of polars in Excel format: NACA63-718.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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA63-618 a=0.8
3. NACA63(3)-618
4. NACA64(3)-618
5. NACA64-618 a=0.8
6. NACA63-719
7. NACA63-717
8. NACA63-518 a=0.8
9. NACA63-618
10. NACA64-717
11. NACA63-619 a=0.8
12. FX 61-184
13. NACA64-719
14. NACA63-617 a=0.8
15. GA 35-418
16. NACA64-619 a=0.8
17. NACA64-518 a=0.8
18. NACA64-617 a=0.8
19. FX 66-17AII-182
20. NACA64-618
21. HQ 3.5/18