Similarly shaped airfoils to NACA64A509
New! Bulk download of polars in Excel format: NACA64A509.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. NACA65-509 a=0.8
3. NACA65A509
4. NACA65-609
5. NACA64-509 a=0.8
6. NACA64-609
7. NACA63-509 a=0.8
8. NACA63-609
9. HQ 3.0/9
10. NACA66A509
11. NACA66-509 a=0.8
12. NACA64-510 a=0.8
13. NACA65-509 a=0.6
14. S7075 (9%)
15. NACA66-609
16. NACA64-610
17. NACA64A510
18. NACA65-510 a=0.8
19. NACA63A510
20. NACA64-509 a=0.6
21. EPPLER 64