Similarly shaped airfoils to NACA67-309 a=0.5
New! Bulk download of polars in Excel format: NACA67-309%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. NACA66-309 a=0.5
3. NACA67-309 a=0.8
4. NACA67A309
5. NACA67-309 a=0.2
6. NACA66-309 a=0.6
7. NACA67-409 a=0.0
8. DP2.00/8.55_DS
9. DP2.05/8.65_DS
10. NACA66-310 a=0.5
11. NACA67-309 a=0.0
12. NACA66-309 a=0.2
13. NACA66-309 a=0.8
14. NACA67-409 a=0.2
15. NACA66A309
16. NACA66-310 a=0.6
17. DP2.06/8.67_DS
18. NACA67-310 a=0.5
19. DP1.87/9.07_DS
20. NACA66-409 a=0.0
21. NACA67-310 a=0.6