Similarly shaped airfoils to NACA65-209
New! Bulk download of polars in Excel format: NACA65-209.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (1) | 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. NACA64-209
3. NACA64A209
4. SM085013
5. NACA63A209
6. NACA65A209
7. NACA65-209 a=0.6
8. NACA64-209 a=0.8
9. NACA65-209 a=0.0
10. NACA65-209 a=0.5
11. NACA63-209
12. NACA65-209 a=0.2
13. NACA66-209
14. HQ 1.0/9
15. NACA64-209 a=0.6
16. NACA65-109 a=0.6
17. NACA65-109 a=0.8
18. NACA64-209 a=0.5
19. NACA63-209 a=0.8
20. NACA64-209 a=0.0
21. NACA64-209 a=0.2