Similarly shaped airfoils to NACA67-609 a=0.8
New! Bulk download of polars in Excel format: NACA67-609%20a%3D0.8.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. NACA67-709
3. NACA66-609 a=0.8
4. NACA66A609
5. NACA66-709
6. NACA66-610 a=0.8
7. NACA67-609 a=0.6
8. NACA66A610
9. NACA65A609
10. NACA67-610 a=0.8
11. NACA67A610
12. NACA66-710
13. NACA65A610
14. NACA67A709
15. NACA67-710
16. NACA66-609 a=0.6
17. NACA67-509 a=0.8
18. NACA67-709 a=0.8
19. NACA66A709
20. NACA66-610 a=0.6
21. NACA67-609 a=0.5