Similarly shaped airfoils to NACA65-409 a=0.0
New! Bulk download of polars in Excel format: NACA65-409%20a%3D0.0.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. NACA64-409 a=0.0
3. NACA64-409 a=0.2
4. FX 69-H-083
5. NACA63-409 a=0.0
6. NACA65-309 a=0.5
7. NACA66-409 a=0.0
8. NACA63-409 a=0.2
9. NACA65-309 a=0.2
10. NACA66-409 a=0.2
11. DP2.06/8.67_DS
12. BOEING 707 .99 SPAN
13. NACA64-309 a=0.5
14. NACA64-410 a=0.0
15. NACA65-410 a=0.0
16. DP2.05/8.65_DS
17. NACA65-309 a=0.6
18. NACA64-309 a=0.2
19. NACA64-410 a=0.2
20. RK40
21. NACA65-410 a=0.2