Similarly shaped airfoils to NACA67-309 a=0.6
New! Bulk download of polars in Excel format: NACA67-309%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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA67-309 a=0.8
3. NACA67A309
4. NACA66-309 a=0.6
5. NACA66-309 a=0.5
6. NACA66-309 a=0.8
7. DP2.00/8.55_DS
8. NACA66A309
9. NACA67-309 a=0.2
10. NACA66-409
11. NACA66-310 a=0.6
12. NACA67-409 a=0.0
13. DP2.05/8.65_DS
14. NACA66-310 a=0.5
15. NACA67-310 a=0.6
16. DP2.06/8.67_DS
17. NACA67-310 a=0.5
18. DP1.87/9.07_DS
19. NACA66-310 a=0.8
20. NACA66A310
21. NACA67-409 a=0.2