Similarly shaped airfoils to NACA64-116 a=0.5
New! Bulk download of polars in Excel format: NACA64-116%20a%3D0.5.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. NACA64-116 a=0.8
3. NACA64-116 a=0.2
4. NACA64-116
5. NACA64-116 a=0.0
6. NACA63-116 a=0.5
7. NACA63-116 a=0.6
8. NACA63-116 a=0.8
9. NACA63-116 a=0.2
10. NACA63-116
11. NACA63-116 a=0.0
12. NACA64-216 a=0.0
13. NACA64-216
14. NACA63-216 a=0.0
15. NACA63A116
16. NACA64-216 a=0.2
17. NACA65-116 a=0.5
18. NACA64-117 a=0.5
19. NACA65-116 a=0.6
20. NACA64-115 a=0.5
21. NACA64-117 a=0.6