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