Similarly shaped airfoils to NACA64-709 a=0.5
New! Bulk download of polars in Excel format: NACA64-709%20a%3D0.5.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. NACA65-709 a=0.5
3. NACA64-709 a=0.6
4. NACA63-709 a=0.6
5. NACA65-709 a=0.6
6. NACA64-710 a=0.5
7. NACA63-710 a=0.5
8. NACA64-710 a=0.6
9. NACA63-710 a=0.6
10. NACA65-710 a=0.5
11. GA 37-610
12. NACA66-709 a=0.5
13. GA 35-610
14. NACA65-710 a=0.6
15. GOE 287
16. NACA64-609 a=0.5
17. GOE 610 B
18. GOE 117 (MVA MK.4)
19. NACA64-609 a=0.6
20. GOE 326 (PFALZ 55)
21. NACA63-609 a=0.5