Similarly shaped airfoils to NACA65A709
New! Bulk download of polars in Excel format: NACA65A709.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. NACA66A709
3. NACA66-709 a=0.8
4. NACA65-709 a=0.8
5. NACA63A709
6. NACA65-710 a=0.8
7. NACA64-709 a=0.8
8. NACA64A710
9. NACA65A710
10. NACA67A709
11. NACA67-709 a=0.8
12. NACA63A710
13. NACA64-710 a=0.8
14. NACA63-709 a=0.8
15. NACA66-609 a=0.8
16. FX 74-080
17. NACA66A710
18. NACA65-609 a=0.8
19. NACA66-710 a=0.8
20. NACA5509
21. NACA63-710 a=0.8