Similarly shaped airfoils to NACA65A509
New! Bulk download of polars in Excel format: NACA65A509.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. NACA65-509 a=0.8
5. NACA66-609
6. NACA65-609
7. NACA63A509
8. NACA64-509 a=0.8
9. NACA65-510 a=0.8
10. NACA64A510
11. NACA65-610
12. NACA64-609
13. NACA65A510
14. NACA66-509 a=0.6
15. NACA65-509 a=0.6
16. NACA67A509
17. NACA67-509 a=0.8
18. NACA63A510
19. NACA64-510 a=0.8
20. NACA63-509 a=0.8
21. NACA64-610