Similarly shaped airfoils to NACA65-711 a=0.8
New! Bulk download of polars in Excel format: NACA65-711%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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2. NACA64-711 a=0.8
3. NACA63A711
4. NACA65A711
5. NACA63-711 a=0.8
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7. NACA65-712 a=0.8
8. NACA65-710 a=0.8
9. NACA66-711 a=0.8
10. NACA64A710
11. NACA66A711
12. NACA64-712 a=0.8
13. NACA63A710
14. NACA66-710 a=0.8
15. NACA66A710
16. NACA65-711 a=0.6
17. NACA64A712
18. NACA63-712 a=0.8
19. NACA64-710 a=0.8
20. S4022
21. NACA63A712