Similarly shaped airfoils to NACA66A509
New! Bulk download of polars in Excel format: NACA66A509.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. NACA66-609
3. NACA65A509
4. NACA67A509
5. NACA67-509 a=0.8
6. NACA65-509 a=0.8
7. NACA65-609
8. NACA66-509 a=0.6
9. NACA64A509
10. NACA65A510
11. NACA66A510
12. NACA66-510 a=0.8
13. NACA65-510 a=0.8
14. NACA66-610
15. NACA65-610
16. NACA63A509
17. NACA66-509
18. NACA67-509 a=0.6
19. NACA64A510
20. NACA65-509 a=0.6
21. NACA66-509 a=0.5