Similarly shaped airfoils to NACA67A509
New! Bulk download of polars in Excel format: NACA67A509.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. NACA66A509
3. NACA66-509 a=0.8
4. NACA66-609
5. NACA67-509 a=0.6
6. NACA66A510
7. NACA66-510 a=0.8
8. NACA65A509
9. NACA66-610
10. NACA67A510
11. NACA67-510 a=0.8
12. NACA65A510
13. NACA66-509 a=0.6
14. NACA67-509 a=0.5
15. NACA67-409 a=0.8
16. NACA67-709
17. NACA67-409 a=0.6
18. NACA66-509
19. NACA66-510 a=0.6
20. NACA67A409
21. NACA67A609