Similarly shaped airfoils to NACA66-309 a=0.6
New! Bulk download of polars in Excel format: NACA66-309%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. NACA66-309 a=0.8
3. NACA66A309
4. DP2.06/8.67_DS
5. NACA66-409
6. NACA67-309 a=0.6
7. DP2.05/8.65_DS
8. NACA65A309
9. NACA67-309 a=0.5
10. DP2.00/8.55_DS
11. DP1.87/9.07_DS
12. NACA65-309 a=0.6
13. NACA65-309 a=0.5
14. NACA67-309 a=0.8
15. NACA67A309
16. NACA66-309 a=0.2
17. NACA65-309 a=0.8
18. DP1.82/8.21_DS
19. NACA66-409 a=0.0
20. NACA66-310 a=0.6
21. NACA66-309