Similarly shaped airfoils to NACA65-118 a=0.8
New! Bulk download of polars in Excel format: NACA65-118%20a%3D0.8.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. NACA65-118
3. NACA65-118 a=0.5
4. NACA65-118 a=0.2
5. NACA65-118 a=0.0
6. NACA64A118
7. NACA65-218
8. NACA65-218 a=0.0
9. NACA63A118
10. NACA65-119 a=0.8
11. NACA65-117 a=0.8
12. NACA65-119 a=0.6
13. NACA65-117 a=0.6
14. NACA65-117
15. NACA65-117 a=0.5
16. NACA65-119 a=0.5
17. NACA65-119
18. NACA65-117 a=0.2
19. NACA65-218 a=0.2
20. NACA65-119 a=0.2
21. NACA64A117