Similarly shaped airfoils to NACA65-509
New! Bulk download of polars in Excel format: NACA65-509.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. NACA64-509
3. NACA64A409
4. NACA64-409 a=0.8
5. NACA65A409
6. NACA63A409
7. NACA63-509
8. NACA65-409 a=0.6
9. NACA66-509
10. NACA63-409 a=0.8
11. NACA66-409 a=0.8
12. NACA66A409
13. HQ 2.5/9
14. HQ 2.5/9 B
15. HQ 2.5/9.0 smoothed by Eppler
16. NACA64-409 a=0.6
17. NACA64-510
18. NACA65-510
19. HN-354OC
20. NACA65-410 a=0.8
21. NACA64-410 a=0.8