Similarly shaped airfoils to NACA64-309 a=0.2
New! Bulk download of polars in Excel format: NACA64-309%20a%3D0.2.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. NACA64-309 a=0.0
3. NACA63-309 a=0.0
4. NACA65-309 a=0.2
5. NACA65-309 a=0.0
6. NACA64-309 a=0.5
7. BOEING 707 .54 SPAN
8. KC-135 BL351.6
9. MH 20 9.01%
10. NACA63-309 a=0.5
11. MH 42 8.94%
12. NACA64-409 a=0.0
13. NACA M11
14. NACA63-409 a=0.0
15. B-29 TIP
16. BOEING 707 .99 SPAN
17. S6061 9%
18. NACA65-309 a=0.5
19. NACA2209
20. NACA64-309 a=0.6
21. NACA2309