Similarly shaped airfoils to NACA67A709
New! Bulk download of polars in Excel format: NACA67A709.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. NACA66A709
3. NACA66-709 a=0.8
4. NACA66A710
5. NACA66-710 a=0.8
6. NACA65A709
7. NACA67A710
8. NACA67-710 a=0.8
9. NACA65A710
10. NACA67-609 a=0.8
11. NACA67-709 a=0.6
12. NACA66-609 a=0.8
13. NACA67A609
14. NACA67-609 a=0.6
15. NACA66-709 a=0.6
16. NACA65-710 a=0.8
17. NACA64A709
18. NACA66A609
19. NACA65-709 a=0.8
20. NACA64A710
21. NACA66-609 a=0.6