Similarly shaped airfoils to NACA63-309 a=0.5
New! Bulk download of polars in Excel format: NACA63-309%20a%3D0.5.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. NACA63-309 a=0.6
3. NACA64-309 a=0.6
4. MS1,9-8,7
5. S6061 9%
6. NACA63-309 a=0.8
7. NACA63-309 a=0.2
8. NACA65-309 a=0.5
9. NACA64-309 a=0.8
10. NACA64-309 a=0.2
11. HN-450S
12. NACA65-309 a=0.6
13. NACA63-409 a=0.0
14. HQ 2.0/9
15. HQ-2.0/9 9.0% smoothed
16. MH 42 8.94%
17. NACA64-409 a=0.0
18. MS2-9,5
19. HN-450
20. S7012 8.75%
21. NACA63-409