Similarly shaped airfoils to NACA66A609
New! Bulk download of polars in Excel format: NACA66A609.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. NACA66-709
3. NACA65A609
4. NACA67A609
5. NACA67-609 a=0.8
6. NACA67-709
7. NACA65-609 a=0.8
8. NACA64A609
9. NACA65-709
10. NACA65A610
11. NACA66A610
12. NACA66-610 a=0.8
13. NACA65-610 a=0.8
14. NACA66-609 a=0.6
15. NACA63A609
16. NACA66-710
17. NACA65-710
18. NACA64A610
19. NACA66-509 a=0.8
20. NACA67-609 a=0.6
21. NACA66-509 a=0.6