Similarly shaped airfoils to NACA63-609 a=0.6
New! Bulk download of polars in Excel format: NACA63-609%20a%3D0.6.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. NACA63-609 a=0.5
3. NACA64-609 a=0.5
4. NACA65-609 a=0.6
5. NACA65-609 a=0.5
6. DAE-51
7. NACA63-610 a=0.6
8. GOE 117 (MVA MK.4)
9. NACA64-610 a=0.6
10. NACA63-609 a=0.8
11. NACA64-609 a=0.8
12. GA 35-610
13. MH 38 9.68%
14. GA 37-610
15. NACA63-610 a=0.5
16. NACA64-610 a=0.5
17. NACA4409
18. NACA63A609
19. NACA65-609 a=0.8
20. GOE 116 (MVA MK.3)
21. HOBIE