Similarly shaped airfoils to NACA65-710 a=0.6
New! Bulk download of polars in Excel format: NACA65-710%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. NACA65-710 a=0.5
3. NACA63-710 a=0.6
4. NACA64-710 a=0.5
5. NACA66-710 a=0.6
6. NACA65-711 a=0.6
7. NACA65-709 a=0.6
8. NACA64-711 a=0.6
9. NACA66-709 a=0.6
10. NACA63-710 a=0.5
11. NACA66-710 a=0.5
12. NACA65-709 a=0.5
13. GOE 392
14. GA 40A610
15. GA 40-610
16. NACA65-711 a=0.5
17. NACA65-710 a=0.8
18. NACA66-709 a=0.5
19. NACA63-711 a=0.6
20. GA 37A610
21. NACA64-711 a=0.5