Similarly shaped airfoils to NACA64A116
New! Bulk download of polars in Excel format: NACA64A116.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. NACA65-116 a=0.8
3. NACA65-116 a=0.6
4. NACA65-116
5. NACA65-116 a=0.5
6. NACA65-116 a=0.2
7. NACA65-116 a=0.0
8. NACA65A116
9. NACA64A117
10. NACA64A115
11. NACA63A115
12. NACA64-116 a=0.8
13. NACA64-116 a=0.6
14. NACA65-216
15. NACA64-116
16. NACA64-116 a=0.5
17. NACA65-117 a=0.8
18. NACA65-117 a=0.6
19. NACA65A115
20. NACA65-117
21. NACA63A117