Similarly shaped airfoils to NACA65-517
New! Bulk download of polars in Excel format: NACA65-517.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. NACA64A417
3. NACA65-417 a=0.6
4. GA 40-317
5. GA 40A317
6. NACA63A417
7. NACA65-518
8. NACA65-516
9. NACA65-416 a=0.8
10. NACA64-517
11. NACA65-418 a=0.8
12. NACA65-417
13. NACA65-617
14. NACA65A417
15. NACA65-417 a=0.5
16. GA 37A317
17. NACA64-417 a=0.8
18. NACA64A416
19. NACA65A416
20. NACA65-517 a=0.8
21. NACA63A416