Similarly shaped airfoils to NACA65-717
New! Bulk download of polars in Excel format: NACA65-717.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. NACA64A617
3. NACA65-718
4. NACA65-716
5. NACA63A617
6. NACA64-717
7. NACA65-517 a=0.8
8. NACA65-617
9. NACA65-618 a=0.8
10. NACA64-617 a=0.8
11. NACA65-616 a=0.8
12. NACA65A617
13. NACA64A616
14. EPPLER 1200
15. NACA65A616
16. NACA63A616
17. NACA64-718
18. NACA65-517 a=0.6
19. NACA65-617 a=0.6
20. GA 40-417
21. NACA64-618 a=0.8