Similarly shaped airfoils to NACA63-118
New! Bulk download of polars in Excel format: NACA63-118.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. NACA63-118 a=0.6
3. NACA63-118 a=0.5
4. NACA63-118 a=0.2
5. NACA63-118 a=0.0
6. NACA64-118
7. NACA64-118 a=0.8
8. NACA64-118 a=0.6
9. NACA64-118 a=0.5
10. NACA64-118 a=0.2
11. NACA64-118 a=0.0
12. NACA63-018
13. NACA63(3)-018
14. GA 35-018
15. NACA63-119
16. NACA63-117
17. NACA63-119 a=0.8
18. NACA64-018
19. NACA63-117 a=0.8
20. NACA63-218
21. NACA63-119 a=0.6