Similarly shaped airfoils to NACA65A516
New! Bulk download of polars in Excel format: NACA65A516.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. NACA66A516
3. NACA66-516 a=0.8
4. NACA66-616
5. NACA65-516 a=0.8
6. NACA65A517
7. NACA65A515
8. NACA65-616
9. NACA65-517 a=0.8
10. NACA64A517
11. NACA66A515
12. NACA66-515 a=0.8
13. NACA65-617
14. NACA63A516
15. NACA66-615
16. NACA66-516 a=0.6
17. NACA65A416
18. NACA65A616
19. NACA65-516 a=0.6
20. GA 37A416
21. GA 40A416