Similarly shaped airfoils to NACA65-712 a=0.8
New! Bulk download of polars in Excel format: NACA65-712%20a%3D0.8.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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3. NACA64-712 a=0.8
4. NACA65A712
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6. NACA65-713 a=0.8
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8. NACA63-712 a=0.8
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10. NACA64-713 a=0.8
11. NACA63A711
12. NACA66-712 a=0.8
13. NACA66A712
14. NACA66-711 a=0.8
15. NACA66A711
16. NACA65-712 a=0.6
17. NACA64A713
18. NACA63-713 a=0.8
19. NACA64-711 a=0.8
20. NACA63A713
21. NACA65-612 a=0.8