Similarly shaped airfoils to NACA65A117
New! Bulk download of polars in Excel format: NACA65A117.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. NACA66-117 a=0.8
3. NACA66A117
4. NACA66-117 a=0.6
5. NACA66-117
6. NACA66-117 a=0.5
7. NACA65A118
8. NACA65A116
9. NACA66-117 a=0.2
10. NACA65-117 a=0.8
11. NACA65-117 a=0.6
12. NACA66-117 a=0.0
13. NACA65-117
14. NACA65-117 a=0.5
15. NACA65-117 a=0.2
16. NACA64A118
17. NACA65-117 a=0.0
18. NACA65-118 a=0.8
19. NACA66A116
20. NACA66-116 a=0.8
21. NACA65-118 a=0.6