Similarly shaped airfoils to NACA63A509
New! Bulk download of polars in Excel format: NACA63A509.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. NACA64-509 a=0.8
3. NACA65-509 a=0.8
4. NACA64-609
5. NACA65-609
6. NACA63-509 a=0.8
7. NACA65A509
8. NACA63-609
9. HQ 3.0/9
10. S7075 (9%)
11. NACA64-510 a=0.8
12. EPPLER 64
13. NACA64-610
14. NACA63-510 a=0.8
15. NACA63-610
16. NACA63A510
17. NACA64A510
18. NACA64-509 a=0.6
19. NACA65-509 a=0.6
20. S4053
21. NACA65-510 a=0.8